CN106233109B - The method for determining the waveguide temperature of the acoustic transceiver for gas-turbine unit - Google Patents
The method for determining the waveguide temperature of the acoustic transceiver for gas-turbine unit Download PDFInfo
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- CN106233109B CN106233109B CN201580021136.3A CN201580021136A CN106233109B CN 106233109 B CN106233109 B CN 106233109B CN 201580021136 A CN201580021136 A CN 201580021136A CN 106233109 B CN106233109 B CN 106233109B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K11/00—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00
- G01K11/22—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using measurement of acoustic effects
- G01K11/24—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using measurement of acoustic effects of the velocity of propagation of sound
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
- G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
- G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
- G01K13/024—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow of moving gases
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- Acoustics & Sound (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
Abstract
A method of for determining the waveguide temperature of at least one waveguide of transceiver, the waveguide temperature is for generating hygrogram.Transceiver generates acoustic signal, which passes through the measurement spatial in the hot gas flow path limited by wall, which is, for example, the wall in burner.This method comprises: calculating the total flight time of acoustic signal；And the waveguide propagation time is subtracted from total flight time to obtain measurement space propagation time.Hygrogram is calculated based on measurement space propagation time.The wall temperature of estimation is obtained according to hygrogram.The waveguide temperature of estimation is then calculated based on the wall temperature of estimation, wherein when determining the waveguide temperature of estimation, do not use temperature-sensing device.
Description
Cross reference to related applications
The application is on April 9th, 2015 is submitting, U.S. Application No. 14/682,393, entitled " PARAMETER
The continuation portion of the Co-pending U.S. Patent Application of DISTRIBUTION MAPPING IN A GAS TURBINE ENGINE "
Point, the full content of the U.S. Patent application is incorporated herein by reference and this application claims the preferential of the U.S. Patent application
Weigh equity.The application requires the entitled " Temperature submitted on April 23rd, 2014 according to 35U.S.C. § 119 (e)
The U.S. Provisional Patent Application No.61/983 of Distribution Mapping in a Gas Turbine Combustor ",
The full content of 044 equity, the U.S. Provisional Patent Application is incorporated herein by reference and this application claims the U.S. to face
When patent application benefit of priority.
The application is incorporated to the full content of the U.S. utility patent application of following co-pending by way of reference, all right
As these U.S. utility patent applications are fully stated herein:
The Serial No. 14/341,950 submitted on July 28th, 2014, entitled " Nonintrusive
The U.S. utility patent Shen of Performance Measurement of a Gas Turbine Engine in Real Time "
Please；
In on July 28th, 2014 is submitting, Serial No. 14/341,924, entitled " Nonintrusive
Transceiver and Method for Characterizing Temperature and Velocity Fields in
The U.S. utility patent application of a Gas Turbine Combustor "；
The Serial No. 14/207,741 submitted on March 13rd, 2014, entitled " Active Measurement Of
The U.S. utility patent application of Gas Flow Temperature, Including In Gas Turbine Combustors "；
The Serial No. 14/132,001 submitted on December 18th, 2013, entitled " Active Temperature
The U.S. utility patent application of Monitoring In Gas Turbine Combustors "；
The Serial No. 14/109,992 submitted on December 18th, 2013, entitled " Multi-Functional
The U.S. utility of Sensor System For Gas Turbine Combustion Monitoring And Control " is special
Benefit application；
The Serial No. 13/804,132 submitted on March 14th, 2013, entitled " Temperature
The U.S. utility patent application of Measurement In AGas Turbine Engine Combustor "；And
The Serial No. 12/967,148 submitted on December 14th, 2010, Publication No. US2012/0150413, title
For the U.S. utility patent application of " Gas Turbine Engine Control Using Acoustic Pyrometry ".
The application is also incorporated with the entitled " Combustion announced on December 14th, 2010 by way of reference
The United States Patent (USP) 7 of Anomaly Detection Via Wavelet Analysis Of Dynamic Sensor Signals ",
853,433 full content just looks like that the United States Patent (USP) has carried out fully statement equally herein.
Explanation about federally funded research or development
Temperature map part of the invention is according to the contract DE-FC26-05NT42644 authorized by U.S. Department of Energy in political affairs
Support lower progress in mansion.Government can have certain right to the present invention.
Background technique
1. invention field
The present invention relates to the mapping of the parameter in the two-dimensional space in the flow region of gas-turbine unit and and relate to
And the active measurement of the flow parameter of such as gas flow temperature or rate in the flow region of gas-turbine unit etc.These
Engine includes industrial gas turbine (IGT) engine, other kinds of stationary gas propeller for turboprop by way of example
Machine, ocean gas-turbine unit, aero gas turbine engine and other vehicle fuel turbogenerators.More specifically, this
Embodiment disclosed herein discloses a kind of method for determining the waveguide temperature of at least one waveguide, to include boundary
The influence of wall temperature and waveguide temperature to the Temperature Distribution of hygrogram, wherein this method includes that the wall temperature based on estimation calculates
The waveguide temperature of estimation, and wherein, when determining the wall temperature of estimation, do not use temperature-sensing device.
2. the description of the prior art
Gas turbine for example, for the gas-turbine unit of any final application etc generally includes compressor section
Point, combustor section, turbine portion and discharge portion.In operation, compressor section sucking and compression environment air.Burner
Part usually may include multiple burners, and the multiple burner is for receiving compressed air and by the compressed air and combustion
Material is mixed to form fuel/air mixture.Fuel/air mixture by each burner in burner burn with
Hot working gas is formed, which can be sent to turbine portion by fixed route, in turbine portion, hot work gas
Body expands through into the static airfoil and rotating airfoils part of alternate row, and for generating the power that can drive rotor.From
The expanding gas for opening turbine portion can be discharged via discharge portion from engine.
It is known that there are abnormal combustions, such as flame flash back in the combustion parts of gas-turbine unit.Flame flash back is to work as
The turbulent combustion rate of the mixture of air and fuel can caused part when being more than the axial flow rate in burner assembly
Phenomenon, thus make flame rest in burner assembly/around one or more components on, for example, rest on around combustion
On the bushing for burning room setting.If backfire situation is kept for the extended period, without being corrected, then the flame stopped can be burnt
Wear each component.Therefore, flame flash back and/or other abnormal combustions will lead to the undesirable damage to burn engines component
And be possibly even to damage, so that needing that these components are placed under repair or replaced.
Fuel/air mixture at each burner is controlled during the operation of engine, will be one or more
A operating characteristic is maintained within a predetermined range, and such as, such as keeps desired efficiency and/or power output, control pollutant water
It puts down, prevent pressure oscillation and prevent from stopping working.In the control device of known type, volume turbine exhaust gas temperature is also used as
Parameters described below is monitored: the parameter can be used for being monitored the operation conditions of engine.For example, controller can be to measuring
Turbine exhaust gas temperature be monitored, and the temperature change measured at discharge portion will lead to controller and change engine
Operation conditions.In the control device of other known types, discrete skin support static probe or porous pressure detector by with
Determine the airflow rate of specific location, but the grid array of these detectors upsets air-flow and introduce measurement error.
Since these air-flows are upset, grid array detector being spaced apart farther out with limited quantity in application, these detections
Device provides the airflow rate distribution and profile information of relative coarseness.
It is currently, there are several different types of sensor and sensing system, these sensors and sensing system are in industry
In for monitor burning and keep combustion process stability with for engine protection.For example, dynamic pressure transducer is used for
Combustion stability and resonance control.Passive vision (optically visible light and/or infrared spectroscopy) sensor, ion transducer and lid
Leather Miller (Geiger Mueller) detector be used to detect the kindling in burner/flame-out, and thermocouple is used for backfire
Detection.About known combustion-gas flow rate (u) monitoring method, skin support static probe and porous pressure detector use differential pressure
Technology, hot-wire detector uses hot wind speed determination techniques, and laser doppler velocimeter system and particle image speed-measuring system are adopted
Airflow rate is characterized with optical technology.Differential pressure instrument and hot wind speed determining instrument are intrusive point measuring devices and upset instrument
Local air flow around device.Laser Doppler Velocimeter device and particle image velocimeter device each provide the measurement of non-intrusion type point
It is measured with two dimension or three-dimensional non-intrusion type airflow rate, but these instruments require to introduce particle to flowing.In addition, complicated
Be used to based on the measurement of laser as filtered Rayleigh scattering (FRS) and the technology other based on laser spectroscopy
Measure gas velocity.However, these technologies are more complicated than intrusive differential pressure instrument or hot wind speed determining instrument and need more professional
Training to implement in monitoring system.In addition, for rate most of optical technologies towards laboratory environment not face
The operation engine of power plant field position.About temperature (T) monitoring technology, it is known that Raman spectroscopy instrument system, laser lures
Lead fluorescent instrument system (for both u monitoring and T monitoring) and relevant anti stokes raman spectrum (CARS) instrument system
(for both u monitoring and T monitoring) also tends to use for laboratory environment not for the scene of fossil generating equipment.
Tunable diode laser absorption spectroscopy (TDLAS) instrument is used in the application in some industrial generation fields, as in boiler
Temperature measurement, but the instrument is extremely expensive: each system is about $ 500,000.Other kinds of temperature measurement and burning
Abnormality detection system has obtained wider approval in power industry field is applied.
Particularly, United States Patent (USP) No.7,853,433 by with sensor --- such as dynamic pressure transducer, accelerometer, height
Warm loudspeaker, optical sensor and/or ion transducer --- to indicate combustion position burning thermal acoustic oscillation be sampled and
Wavelet analysis is carried out, then to be detected and be classified to abnormal combustion.The United States Patent (USP) of Publication No. US2012/0150413
The pyrometry of acoustics is used in a burner in IGT exhaust system in burner to determine engine or more by document
Upstream bulk temperature in multiple burners.Acoustic signal sends from acoustics transmitter and is received by multiple acoustic receivers.
Each acoustic signal limits the different sound ray paths between corresponding transmitter and receiver pair.Determine the signal sent
Flight time and the flight time is handled to determine path temperature.Multiple path temperature can be combined and be located
Reason is to determine the bulk temperature at measurement position.It can use identified path temperature or bulk temperature or utilize path temperature
Degree is associated with the upstream temperature in burner with both bulk temperatures.The U.S. of the co-pending of Serial No. 13/804,132 is real
The bulk temperature in burner is calculated using so-called dominant pattern method, by following manner with patent application: to starting
Choacoustic frequency at the first position of the upstream (such as in burner) positioned at turbine in machine is identified, and utilizes the frequency
Determine the first bulk temperature value, first bulk temperature is directly proportional to choacoustic frequency and the steady state value of calculating.Determine engine
In the second place such as engine exhaust portion at working gas calibration second temperature.It is carried out by the calibration second temperature
Retrospectively calculate is to determine the temperature value of the working gas at first position.The temperature value that first temperature value and retrospectively calculate go out carries out
Compare so that calculated steady state value is changed to the steady state value recalculated.The first subsequent temperature value at burner can be with base
It is determined in the steady state value that recalculates.
In the presence of the demand to following technologies: the technology is used for based on to being averaged along the route between transceiver
Real-time, the X-Y scheme of Temperature Distribution in flow region of the estimation of temperature to create gas-turbine unit, and it is described
Technology includes the influence of boundary wall and waveguide temperature to the Temperature Distribution of two-dimensional temperature map.
There is another demand to the monitoring of following integrated gas turbogenerators and control system in the art: this is
System fails to possible burner on a large scale or more satisfactory for airflow rate, the temperature during measure burning
Ground detects the omen of failure, shares conventional sensor and shares conventional controller in case of need.
Exist in the art to gas-turbine unit active rate (active velocity) and temperature monitoring system
Another demand, which maps Actual combustion device rate and temperature in real time, without from in-engine other positions
Obtain fiducial temperature, for example, as it is known that bulk temperature system, based on the temperature measurement result obtained in engine exhaust system
Retrospectively calculate burner temperature.
In the presence of to actively (active) airflow rate and temperature monitoring system additional demand, the active flow rate and
Temperature monitoring system shares the sensor being usually used together with gas turbine monitoring and control system, so that active rate and temperature
Degree monitoring can be integrated in monitoring and control system.
In the presence of another demand to following technologies: the technology is provided in the plane of the air-flow in turbogenerator
Real time temperature information is to control engine.
In the presence of the another demand to following technologies: the technology is used for based on along in the plane of combustor flow
The mean temperature of route controls gas turbine burner.
Summary of the invention
Disclose a kind of method for determining the waveguide temperature at least one waveguide being used in combination with transceiver, the wave
Temperature is led for generating gas turbine hygrogram.Transceiver generates acoustic signal, which passes through in hot gas flow path
Spatial is measured, which is such as limited by the wall in burner.This method includes calculating total flight time, wherein
The total flight time includes across the propagation time in measurement space and across the propagation time of waveguide.Then from total flight time
The waveguide propagation time is subtracted to obtain measurement space propagation time.This method further includes calculating temperature based on measurement space propagation time
Degree figure and the wall temperature that estimation is then obtained according to the hygrogram.In addition, this method includes that the wall temperature based on estimation calculates
The waveguide temperature of estimation, wherein when determining the waveguide temperature of estimation, do not use temperature-sensing device.
Furthermore there is disclosed a kind of for determining the side of the waveguide temperature at least one waveguide being used in combination with transceiver
Method, the waveguide temperature is for generating gas turbine hygrogram.Transceiver generates acoustic signal, which passes through hot gas flow path
Measurement spatial in diameter, the hot gas flow path are such as limited by the wall in burner.This method include wall is divided into it is multiple
Boundary part, wherein each boundary part is associated with transceiver and waveguide.This method further includes calculating the total of acoustic signal to fly
The row time, wherein the total flight time includes across the propagation time in measurement space and across the propagation time of waveguide.Then from
The waveguide propagation time is subtracted in total flight time to obtain measurement space propagation time.In addition, this method includes empty based on measurement
Between the propagation time calculate hygrogram and then obtained according to hygrogram each boundary part estimation temperature.In addition, the party
Method includes the waveguide temperature for calculating the estimation of each boundary part, wherein when determining the waveguide temperature of estimation, does not use temperature
Sensing device.
Corresponding object and feature of the invention can be by those skilled in the art in any combination or the mode of sub-portfolio is total to
It applies with ground or respectively.
Detailed description of the invention
It is described in detail below to consider in conjunction with the accompanying drawings, it can be readily appreciated that teachings of the present invention, in the accompanying drawings:
Fig. 1 is the perspective, cut-away view of gas-turbine unit, and it illustrates embodiment according to the present invention for true
Determine the executive mode of the system of combustor air flow active rate and temperature measurement；
Fig. 2 is the sectional view of gas turbine burner, which is combined with embodiment party according to the present invention
The embodiment of the monitoring system for determining combustor air flow active rate and temperature measurement of formula；
Fig. 3 is the sectional view that the 3-3 along Fig. 2 of the system in Fig. 2 of various aspects according to the present invention is intercepted；
Fig. 4 is for the prison measured for determining combustor air flow active rate and temperature in embodiments of the present invention
The block diagram of the embodiment of the controller of embodiments of the present invention is executed in examining system；
Fig. 5 is the exemplary isometric view of the exemplary sonic sensor array of embodiment according to the present invention, the example
Property sonic sensor array be used to measure airflow rate in gas turbine burner by airflow rate monitoring system；
Fig. 6 is sight of the edge between acoustic sensor 32B and acoustic sensor 34C in the turbine burner of Fig. 5
Airflow rate illustrative schematic diagram；
Fig. 7 be Fig. 6 airflow rate along Fig. 6 7-7 intercept cross-sectional segment, 7-7 correspond to acoustic sensor 32B with
Sight between acoustic sensor 34C；
Fig. 8 is that embodiment according to the present invention by the respective rate that measures of airflow rate monitoring system synthesizes air-flow
Rate distribution；
Fig. 9 is embodiment according to the present invention for measuring to the gas flow temperature in gas turbine burner
The schematic perspective view of exemplary sonic sensor array；
Figure 10 is to show the flow chart of the embodiment for the method for executing embodiment according to the present invention: this method is used
Airflow rate and temperature in measurement gas turbine burner actively measure；And
Figure 11 is to show the reality for the method for measuring active flow rate for executing embodiment according to the present invention
Apply the flow chart of mode.
Figure 12 is the schematic diagram of the gas-turbine unit of embodiment according to the present invention, and it illustrates several substitutions
Property region in sensor installation.
Figure 13 is the flow parameter in the region for mapping gas-turbine unit of embodiment according to the present invention
System schematic diagram.
Figure 14 A is the schematic diagram that the bilinearity of the parameter along path of embodiment according to the present invention indicates.Figure 14 B
It is the schematic diagram of the two-dimensional space for the path profile of embodiment according to the present invention indicated with bilinearity.
Figure 15 be show embodiment according to the present invention for the technology based on average path value mapping parameters
Flow chart.
Figure 16 is to show the diagram of the parameter profile in single path of embodiment according to the present invention.
Figure 17 be show embodiment according to the present invention for the technology based on average path value mapping parameters
Flow chart.
Figure 18 is the schematic diagram of the two-dimensional space of embodiment according to the present invention, and it illustrates measuring routes and lattice portion
Point.
Figure 19 be show embodiment according to the present invention for the technology based on average path value mapping parameters
Flow chart.
Figure 20 is the exemplary sectional view of multiple transceivers, and each transceiver all has waveguide, wherein transceiver is each self-produced
Raw acoustic signal, the acoustic signal limit multiple acoustic paths of the measurement spatial across hot gas flow path.
Figure 21 depicts the boundary part for limiting the wall of hot gas flow path, wherein the wall is divided into multiple virtual sides
Boundary part, each virtual boundary part all have associated transceiver and waveguide.
Figure 22 depicts the boundary part of wall, which is not divided and including the transceiver with waveguide.
Figure 23 is to show the flow chart of the method for determining waveguide temperature of embodiment according to the present invention.
Figure 24 is to depict the curve graph of the exemplary waveguide temperature curve of each waveguide shown in Figure 20.
Figure 25 to Figure 30 depicts a series of exemplary temperature figure, these exemplary temperatures are shown with iteration time
Number increases and the temperature convergence of the waveguide of progress.
In order to make it easy to understand, in the conceived case, being indicated using identical appended drawing reference identical common to each figure
Element.
Specific embodiment
After considering to be described below, those skilled in the art be will readily recognize that, teachings of the present invention can be held
It changes places for active acoustics speed measurement and the airflow rate based on pyrometry measures and temperature measurement.Of the invention
Embodiment is used to supervise the gas turbine burner for including industry gas turbine (IGT) burner by following manner
It surveys: gas turbine burner being integrated to combustion monitoring and control system by means of addition acoustics transmitter or acoustic transceiver
In, acoustics transmitter or acoustic transceiver are sent out along sight across air-flow by multiple acoustic sensors such as dynamic pressure transducer
Send sound wave.For speed measurement, the voice transmission flight time, --- it passes through air flow path and is substantially transversely directed toward --- was by controlling
Device processed measurement and associated with along the airflow rate of sight.The determination of airflow rate include with regard to the relevant temperature of thermodynamics,
The influence of gas constant and the velocity of sound to the first flight time compensates, to determine absolute air flow rate.
In the sensor and monitoring/control system embodiment based on acoustic stress of integral type, controller makes speed
Rate and make if necessary absolute active path (absolute active path) temperature simultaneously with acoustic transmission analytical technology
It is contacted with ToF analysis technology.In the case where measuring rate and temperature at the same time, absolute active path temperature by with
To compensate the above-mentioned thermodynamic effects to air-flow absolute speed.Alternatively, in other embodiments, the velocity of sound is flown to first
The influence of time is used to determine absolute air flow rate rather than absolute active path temperature.In these embodiments, in rate
Realized to the compensation of the velocity of sound by following manner in monitoring: use can send and receive acoustic signal and generate output signal
One group of first transceiver/energy converter replaces the first transmitter, and with can send and receive acoustic signal and generate output
One group of second transducer of signal replaces first sensor.Acoustic signal, which is sent and received from first transducer to second, to be changed
It can be determined device and flight time.Reversed acoustic signal is sent and is received from second transducer to first transducer and anti-
To flight time be determined.Corresponding first acoustic signal flight time and the first reversed acoustic signal flight time are used for
Determine velocity of sound c.Identified velocity of sound c is used to determine actual airflow rate.
In embodiments of the present invention, active speed measurement or active rate/temperature measurement are in combustion monitoring and control
It is used as the monitoring parameters for air-flow in system, the combustion monitoring and control system can be for example by using wavelet analysis skills
Art or Fourier analysis technology identify air-flow abnormal (for example, abnormal combustion) and classify extremely to air-flow.The method
Some embodiments with the system include one or more acoustics dynamic pressure transceiver/energy converters and transmitter/sensing
The combination of device, the transmitter/sensor are selectively oriented or are arranged in burner in continuous axial flat position.
In the past, in power field in use, known transceiver/transducer element design and its relevant controller part by
Reliably and cost-effectively use.By the way that the known elements of these types to be reconfigured to gas flow optimized and prison of the invention
In examining system, gas turbine and other combustion-type generating equipments can be configured by simpler instrument hardware being monitored and
Control, the instrument hardware configuration provide the detailed active flow rate and Temperature Distribution useful to accurate Combustion System
Information.
Monitoring and Control system architecture
Referring to Figures 1 and 2, it illustrates illustrative industrial gas turbine engines 10.Illustrative engine 10 wraps
Include compressor section 12, combustor section 14, turbine portion 16 and discharge portion or exhaust system 18.Combustor section 14 wraps
Include multiple burners 20.Each burner 20 all has burner shell 22 and cover board 24.26 He of combustion liner or burner inner liner
Coupling tube 27 limits the channel for transmitting hot working gas, which flows to turbine portion 16 along direction F.This hair
Bright system can be designed by means of the gas-turbine unit of known burner geometry to operate, including static base
Burner, the burner of circular pipe type configuration or the burning of loop configurations of tubular configuration in the application on land or vehicle application
Device.
During the operation of engine 10, the compressed air from compressor section 12 is supplied to combustor section 14,
In combustor section 14, which mixes with the fuel supplied by the fuel injection system 28 in burner 14.Fuel/
Air mixture is ignited to form the combustion product including hot working gas.It is understood that can be along across combustion
Fuel occurs at burner bushing or burner inner liner 26 and coupling tube 27 to the axially different position in the channel of the entrance of turbine portion 16
With the burning of air.Thermal technology makees gas expansion and is discharged across turbine portion 16 and by discharge portion/exhaust system 18.
Referring to Figures 1 and 2, according to aspects of the present invention, a kind of combustion monitoring and control system 29 are provided, can be known
Other abnormal combustion and classify to abnormal combustion, and to one or more burnings in the burner of engine 10 20
Gas turbine combustion process in device 20 carries out active control.In this respect, engine 10 may include following monitoring and control
One of system 29 or more person: for example, the system 29 or individual system 29 for each burner 20 can be
Each burner 14 of engine 10 services.Similarly, the cluster of burner 20 can be serviced by a system 29, and other
Cluster is serviced by other systems.Therefore, regardless of engine design uses which type of engine burner structure or orientation: hair
Motivation design is turbogenerator static, land based or the vehicle hair for the application of aviation, ocean or land vehicle
Motivation, the comprehensive monitor system for engine 10 can determine the deviation between related burner and to these burners
Correlated performance be compared.
As shown in Fig. 2, Fig. 3, Fig. 5 and Fig. 9, system 29 includes multiple known acoustic transceiver/energy converter 32A
To 32H and acoustic transceiver/energy converter 34A to 34H array, these acoustic transceiver/energy converters can along in Fig. 5 and
Illustrative sight line path shown in dotted line sends and receives acoustic oscillations wave in Fig. 9.Transceiver/transducer array 32,34
Corresponding sensor output signal can be generated, the instruction of these sensor output signals is each corresponding monitored and controlled
Burning thermal acoustic oscillation in burner 20.The other embodiments of the system can be configured to have at least two acoustics sensors
Device but preferably have more acoustic sensors, these acoustic sensors be functionally transceiver components a part or
As individual components.It is produced due to the combustion incident in work burning gases by those of transceiver acoustic sensor part
The choacoustic frequency and amplitude of sensing, to limit the sound source being present in the hot gas path of burner 20.Monitoring and control system
The system 29 thermal acoustic oscillation information that is configured to sense, which is transformed into, can carry out interested abnormal combustion to distinguish
Form.It therefore, can be according to by being located at transceiver/energy converter/sensor in burner 14 and/or around burner 14
The thermal acoustic oscillation sensed in the burner 14 of monitoring detects and infers interested flame flash back event and other types
Abnormal combustion.According to the configuration and application of system 29, acoustic sensor includes dynamic pressure transducer, loudspeaker, optics biography
Any combination of one of sensor or ionic formula turbine inlet sensor or more person.Pressure sensor is in burner 20
The amplitude and ripple frequency of thermal acoustic oscillation are sensed.High temperature loudspeaker can be used for measuring the acoustic wave in burner 14
It is dynamic.Optical sensor can be used for measuring the dynamic optical signal in burner 20.Ion transducer can be used for measuring burning
Dynamic ion activity in device 20.
The illustrative acoustic sensor array schematically shown in Fig. 2, Fig. 3, Fig. 5 and Fig. 9 includes transceiver/change
Can device 32A to 32H and transceiver/energy converter 34A to 34H, these transceiver/energy converters at least one of are used as with array
And at least one acoustics transmitter that preferably multiple dynamic pressure transducers are transmitted.Transceiver/energy converter 32,34 is logical
It crosses known mounting structure and method such as J-type pipe or rake (J tubes or rakes) and is arranged in burning axially and radially
In device 20, and close to burner flame cylinder or bushing 26 in the burner shell 22 and/or close with turbine portion 16
In conjunction with transition part 27.In Fig. 3, sensor is radially/transceiver 34A to 34H for circumferentially arranging, and transceiver 34A is extremely
34H can send and connect along the sight line path similar with the sight line path of transceiver 32A to 32H shown in dotted line in Fig. 9
It quiets down and learns oscillation wave.Other kinds of known sensor --- such as individual thermocouple temperature sensor or thermocouple arrays ---
It can be used in gas-turbine unit.For example, thermocouple 36 carries out the ignition temperature in burner 20 in Fig. 3
Measurement.The two-dimentional circular ring shape that although illustrative three-dimensional ring combustion flows path is shown in the attached drawings and is axially spaced
Transceiver/transducer array, but can also be used when implementing embodiments of the present invention other combustion flows paths and
Array orientation, the geometry including square configuration or rectangular shape.
As illustrated in greater detail in figs. 3 and 4, monitoring and control system 29 include being attached to transceiver/energy converter
32,34 known controller 40, controller 40 can make in monitoring part 42 sensor output signal and airflow rate and
Ignition temperature is associated and the analysis of the kinetics of combustion of combustion process can be carried out in analysis part 44.Monitor part 42
Output and the output of dynamic analysis part 44 are used by gas turbine control system 46, and gas turbine control system 46 can be with
To other gas turbine control subsystems including industry gas turbine (IGT) control subsystem --- such as, fuel injection
System 28 --- control signal is sent, unloads or closes with variation in response to the combustion position monitored in burner 20
Engine 10.
The embodiment of the illustrative controller 40 referring to fig. 4 gone out, controller 40 include one or more
Processor 50, system storage 52 and input/output control device (I/O) 54, so as to the control of associated engine 10
Device --- such as, fuel injection control apparatus 28 --- and acoustic transceiver/energy converter 32,34, acoustics transmitter and sensor
32 (or the individual discrete transmitters and receivers sensors for executing identical functions), other computing devices, are used for network
The connection of the interfaces such as operator/user man-machine interface.Controller 40 can also include one or more analog-digital converters (A/D)
56A and/or permission controller 40 are connect with transceiver 32,34 and/or other systems unit interface to receive the sensor of simulation
Other component needed for information.Alternatively and/or in addition, system 29 may include one or more analog-digital converter 56B,
Analog-digital converter 56B (or executes the individual discrete transmitters and receivers sensing of identical functions in transceiver 32,34
Device) and controller 40 between carry out interface connection.As another example, certain transceivers 32,34, which can have, is integral with
Analog-digital converter 56C, or the digital representation of the information sensed can be sent directly to controller 40.
Processor (multiple processors) 50 may include one or more processing units, such as general purpose computer, microcomputer
Calculation machine or microcontroller.Processor 50 can also include one or more processing units, programmable and/or Reprogrammable skill
Art and/or special-purpose member, processing unit are, for example, central processing unit, dedicated digital signal processor (DSP), be may be programmed
And/or Reprogrammable technology and/or special-purpose member be, for example, specific integrated circuit (ASIC), programmable gate array (e.g., PGA,
FPGA)。
Memory 52 may include for the computer program code that can be executed by processor (multiple processors) 50
The region stored and the region for being stored to the data being used for the treatment of, for the data being used for the treatment of
The region stored is, for example, for holding to wavelet transformation, Fourier transform or for running monitoring and control system 29
The memory area that other capable mathematical operations are calculated, as being more fully described herein below.Therefore, of the invention
Various aspects may be performed that the computer program product with following codes: the code configuration at execute to interested hair
The detection that motivation abnormal combustion, kinetics of combustion and engine control function carry out, as stated in more detail herein.
In this respect, processor (multiple processors) 50 and/or memory 52 are programmed with enough codes, variable, match
File etc. is set, so that controller 40 is able to carry out its specified monitoring and control function.For example, controller 40 can be operatively
It is configured to sensing thermoacoustic situation, thermoacoustic shape is analyzed based on the input from one or more transceiver/energy converters 32,34
Condition, controls the characteristic of engine 10 in response to the analysis of controller 40, and/or to operator, user, other computers
The analysis of the Reporting Controllers such as processing unit 40 as a result, as stated in more detail herein.Therefore, from transceiver/change
All dynamical output signals of energy device 32,34 can be sent to single processor 50.In this executive mode, single processor
50 will handle sensor dynamical output signal using the data analysis and control function that are more fully described herein, so that seeing
Get up is like result with the calculating of substantially parallel form.Alternatively, more processors 50, and such as root can be used
According to the computing capability of such as each processor, each processor be may be incorporated for one or more transceiver/energy converters 32,34
Dynamic Signal handled.
Monitoring and control system operation
Both the concept of the measurement of acoustics temperature and speed measurement is based on generating sound wave, monitors sound wave across air-flow and ask
The bulk sound velocity by given path is obtained, which is used subsequently to description gas velocity or rate/temperature.Figure 10 and Figure 11
It is the flow chart of the exemplary operation for the monitoring and control system 29 for diagrammatically illustrating embodiments of the present invention, prison
It surveys and control system 29 is initiatively monitored using acoustic measurement method and measures airflow rate and temperature.Heavy line operating block and void
Line operating block be related to the function (solid blocks) of previously described kinetics of combustion analysis 42, temperature monitoring and determine 44 function and
The function (by way of example including IGT control function) of gas turbine control 46, these functions are all held in controller 40
Row.In step 100, to by the sensor element in transceiver/energy converter 32A to 32H, transceiver/energy converter 34A to 34H
The sensor signal of generation is read out.In step 110, by one or more sensor signals in sensor signal
Amplitude is compared with the alarm limit previously established.For example, in IGT application, in the step 120, due to engine speed
50Hz or the potential resonance of 60Hz influence, the low frequency kinetic characteristics (LFD) lower than 100Hz are critically important.It is interested other
Frequency band is approximation 100Hz to the intermediate frequency kinetic characteristics (IFD) between 500Hz and the high frequency kinetic characteristics higher than 500Hz
(HFD).If alarm limit is exceeded, controller 40 for example sends control to fuel injection system 28 in step 400 and refers to
It enables, to unload or close engine 10.
If alarm limit is not exceeded in step 110, in the abnormity detection portion of kinetics of combustion analyzing subsystem
It is executed in point and is used for dynamic (dynamical) frequency analysis.It is described in United States Patent (USP) No.7,853,433 and how to execute abnormality detection
Exemplary description, the United States Patent (USP) are incorporated herein by reference.It is pressed in step 130 from the high speed dynamic that sensor obtains sampling
Force signal, and the high speed dynamic pressure signal of sampling is divided into section with the time in step 140.In step 150, utilize
The wavelet analysis technology described in United States Patent (USP) No.7,853,433 analyzes the sampling section that time-frequency divides.It is alternative
The known Fourier analysis that period is converted into frequency space is passed through identification crest frequency and its corresponding amplitude by ground
It analyzes basic frequency, and identifies to be more than the amplitude for limiting threshold value.If determining that abnormal combustion or more has occurred in a step 160
A abnormal combustion then such as in temperature monitoring and will determine identified burner temperature in subsystem 44 and pass through Fourier analysis
Technology or wavelet analysis technology or the exception information progress obtained by both Fourier analysis technology and wavelet analysis technology
Compare.In step 180, it is divided into kindling, flame-out or backfire anomaly classification combines from temperature monitoring and determines that subsystem 44 obtains
Passive temperature information or path temperature information carry out.For example, when gas turbine stops working, the significant underground of burner temperature
Drop.On the contrary, the burner temperature of the upstream in burner 14 rises in backfire significantly.When in step 180 into
When row abnormal determination, the control signal appropriate to unload or close engine is formed in engine control system 46.
Temperature monitoring and determining subsystem 44 may include the real-time reality in the determination of passive type temperature and/or burner 14
Border path temperature determines that the passive type temperature determines the use of Serial No. 13/804,132, the topic submitted on March 14th, 2013
In U.S. Patent application for " Temperature Measurement in a Gas Turbine Engine Combustor "
Described passive type acoustic method, the U.S. Patent application are incorporated herein by reference.By being to U.S. Patent Publication No.
Combustion turbine exhaustion system is used for described in the patent document of US 2012/0150413 (it is incorporated herein also by reference)
2D (two dimension) plane acoustic thermometry technology that temperature determines is adjusted or determines real-time reality by 3D (three-dimensional) technology
Border path temperature, the 3D technology are determined one or more path temperature between the sensor array 32/34 of Fig. 5,
This is further more fully described herein.
In passive type temperature determining method, in step 200, for dominant pattern to from transceiver/energy converter 32/
34, the high speed dynamic pressure signal of sampling that such as obtains in step 130 analyzed.In step 210, based on frequency,
Burner temperature is calculated using passive type acoustic method.In a step 220, passive value is calibrated by reference temperature value, with
Obtain the active temperature value in burner 14.In step 230, what use determined in a step 220 is calibrated by dynamic temperature
Value is with the ensemble average temperature (bulk mean temperature) of determining burning gases in step 230.Used in step 220
In reference temperature value can be from one or more thermocouples 36 in burner or the thermoelectricity in exhaust system 18
Even (not shown) obtains.It is US2012/ that reference temperature value, which can be measure in exhaust system 18, such as U.S. Patent Publication No.,
Actual path temperature or reference temperature value described in 0150413 patent document can be to be measured in burner 14
, in step 300 to step 330 determine real-time route temperature.
2D real-time route temperature passes through with for example in (n=8) transceiver/energy converter 32A to 32H 2D shown in Fig. 9
Acoustic transceiver/energy converter 32,34 of plane pattern or other discrete transmitters, which send one or more acoustic signals, to be come
It measures.For example, transceiver/energy converter 32A is sent by remaining (n-1) transceiver/energy converter 32B to 32H received signal,
And determine the flight time of each sight line path.However, at least one of remaining transceiver/energy converter 32B to 32H, excellent
Two or more sensor elements of selection of land receive acoustic signal (multiple acoustic signals) in the step 310.Preferably, it is practicing
In, several transceiver/energy converters (it sends and receive acoustic signal) are around a plane so that between all transceivers
Path formed have required roughness grid, with required roughness grid result in temperature measurement spatial discrimination
Rate.For example, transceiver can be equally spaced as shown in Fig. 3 and Fig. 9 around periphery for tubular burner.
The excitation of disjoint acoustic pattern that these transceivers can successively can be readily distinguished (one at a time) or by
It excites simultaneously.For exciting in succession, a transceiver generates sound, and remaining these sound of all transceiver records are to estimate
The propagation time of respective paths.Each sight line path in these sight line paths shows the mean temperature along the path.
The mean temperature on different paths is combined into X-Y scheme shown in Fig. 9 using known computer assisted tomography technology.
In step 320, using active acoustics, for example by being US2012/ using in above-mentioned U.S. Patent Publication No.
2D flight time voice data is converted into gas temperature by method described in 0150413 patent document, and the U.S. is special
Benefit is open to be incorporated herein by reference.Determining real-time route temperature is the part along line-of-sight transmission path in a step 330
Active temperature value.It can be with by executing multiple active temperature values that step 300 is measured to step 330 along different acoustic paths
It is used to concurrently determine the entirety of burner 14 individually or with the dominant frequency passive type acoustic method of step 200 to step 230
Temperature.Although the single path active temperature measurement between single transmitter 30 and acoustic sensor 32 provides useful control
Information, but make multiple transceiver/energy converters 32,34 in burner 14 (see such as Fig. 2, Fig. 3, Fig. 5 or Fig. 9) or in a system
It is selectively arranged in any axialmode, circumferential type, radial mode or combinations thereof in column burner 14 and is also beneficial to gas turbine hair
The Real-time Two-dimensional or Three-dimensional Combustion temperature monitoring of active in motivation 10.
2D the or 3D real-time route temperature determined in step 300 to step 330 may be used as other monitorings and control
The input of functional device processed, other monitorings and control function device are with or without examples described herein integral type
Monitoring and control system 29 described in kinetics of combustion analysis 42 function, passive temperature monitoring and determine 44 function with
And one of function of control 46 or more person.For example, burner turbine-entry temperature (TIT) can be supervised actively in real time
It surveys and is used as the control parameter for combustion process.The burning active path temperature determined in step 300 to step 330
It can be used to control the fuel/air mixture in burner 14 via fuel injection system 28.Real-time route active temperature
It may be used as the active actual airflow speed measurement in industry gas turbine burner or in other kinds of air-flow environment
Input.
Embodiments of the present invention pass through and along positioned at axially spaced, transversal orientation sound transmitter and sensors
The sound wave reflection method of sight sound wave path between (or the transceiver/energy converter for combining sensor and transmitter) is related
Connection is to measure 3D airflow rate and/or gas flow temperature, so that being oriented transverse to air-flow road along the sight in the path
Diameter, without being parallel to air flow path.In order to determine that air-flow absolute speed, time of flight data are just normal to gas temperature, gas
It counts the thermodynamic effects with the velocity of sound and is corrected or is compensated.As noted above, it can use real-time active path temperature
Degree or the temperature that independently obtains from another measuring device (e.g., thermocouple 36) determine the gas temperature along sight.Substitution
Property, local acoustical can be determined by measuring the two-way flight time (that is, forward direction/downstream transmission and reversed/upstream transmission)
Fast c.Above-mentioned thermodynamic effects are determined by following known equations:
C (x, y, z)=(γ .R.T)1/2
Wherein:
C (x, y, z) is the constant entropy velocity of sound；
γ is specific heat ratio；
R is gas constant；And
T is gas temperature.
Therefore, once along the velocity of sound in path be it is known, average path temperature and absolute speed can use the present invention
Embodiment described further herein determine.
Accurate absolute speed or temperature are measured, two planes of transceiver/energy converter 32,34 are in air-flow inner shaft
It is oriented to spaced apart, opposite relationship, as shown in Figure 5.Described two planes of transceiver/energy converter 32,34 are preferably
At a distance of the order of magnitude about the same with the diameter (circle) of air-flow geometry or width (rectangular or rectangle) that are monitored away from
From.That is, the axial distance between the two planes should be according to the geometry and scale and air-flow gas of monitored environment
Constant, the desired extent of temperature and rate or possible range determine.
Airflow rate is estimated, along axially and transverse to flow direction measurement air-flow.For example, working as plane ZⅠIn transmitting-receiving
When device/energy converter 32A excitation or transmission signal, plane ZⅡIn all transmitting-receivings with the not parallel alignment of signal excitation sensor
Device/energy converter 34B to 34H will be monitored, and thus generate several paths across air-flow (for the feelings of n sensor
Condition is n-1 path).Signal transmission/reception excitation process passes through plane ZⅠOn second transceiver/energy converter 32B to reception
A transceiver of residue (the n-1)/energy converter 34A and transceiver/energy converter 34C to 34H of transmitted signal excited and
Sequentially continue.The excitation of transmitted signal will continue, so that continuous transceiver excitation, and n- is generated for excitation every time
1 path.In the embodiment of Fig. 5,8 transmitting-receivings are all had in each array in two axially spaced arrays
Device/energy converter, thus exist into three-dimensional 64 paths of total.In addition, in order to which the direction of reduction speed is uncertain (with identification
Possible turbulent fluctuation in reverse flow and opposite direction), it is assumed that gas flow temperature be it is known, will be by making plane ZⅡIn change
Energy device/transceiver 34 excites and makes plane ZⅠIn transceiver/energy converter receive the acoustic signal that opposite direction is sent and repeat
Identical process.It, can be from each corresponding receipts instead of exciting acoustic signal from each transceiver/energy converter is sequentially sent/
It sends out device/energy converter 32A to 32H, transceiver/energy converter 34A to 34H and sends the sound with slightly different acoustic feature simultaneously
Mode, this shortens time of measuring.The step 500 and step 510 of 1 airflow rate measuring method flow chart referring to Fig.1, once
Plane ZⅠWith plane ZⅡIn all transceiver/energy converters all excited and transmitted acoustic signals are by opposite plane
The transceiver being laterally aligned to/energy converter receives, then preferably continuously repeats the process in real time, while chromatographing using known 3D
Imaging mapping techniques 3D rate diagram u is constructed according to the sight acoustic path of spatial distribution, it is known that 3D tomography map skill
Art be, for example, be used in medical treatment or Industrial Computed Laminography system in those of 3D chromatography imaging technique.Rate information is extracted
And be mapped, as shown in Figure 8.Similarly, 3D hygrogram can use time of flight data to construct, such as will herein more
It describes in detail.
After all transceiver/energy converters 32,34 in planar array have all excited acoustic signal, corresponding sight stream
Dynamic path time of flight data is corrected Yi Dan with regard to the thermodynamic effects of temperature, gas constant and the velocity of sound, then is used in step
The absolute speed in air flow path is obtained in rapid 560, as described in more detail below.Assuming that the gas temperature in speed measurement
Be it is constant, then flow rate measurement accuracy may be decreased when flow rate is close to the velocity of sound.Lower than the stream of about 0.5 Mach number
Dynamic rate is not considered influencing the measurement of rate significantly.Accordingly, it is preferred that but not necessarily, the flow rate measured should
The half of local sonic speed than measuring is small.Although absolute speed is relatively high, this method can be sent out including turbine
The high temperature gas flow of motivation air-flow is accurately measured, this is because local sonic speed increases with temperature.
Once acoustic time of flight data is available, then monitoring and control system 29 or other remote supervision systems use these
Data according to the remaining step in the step of Figure 11 determine the rate along its corresponding acoustic path.Referring to Fig. 6 and figure
7, information voice, which propagates flow of being bullied, linearly to be influenced.For given temperature, the relative wind rate of gas constant and the velocity of sound
It is determined by following known equations:
Wherein:
tBCIt is the flight time from the first transmitter B to first sensor C；
C is the velocity of sound for temperature and gas constant in air-flow；
For along the unit vector of the first sound ray path A between B and C；And
It is the velocity vectors in air-flow.
Simplified flow pattern is shown along the exemplary planar piece of sound ray path A.Referring again to the flow chart of Figure 11, in step
In rapid 560, relative wind rate with regard to thermodynamic temperature, air-flow and the velocity of sound influence and be corrected, to obtain absolute speed.On road
In the case of the available (step 520) of diameter temperature, influence of the path temperature to the velocity of sound can by known chromatography imaging method come
Correction, to obtain the air-flow absolute speed along sound ray path.In the not available situation of path temperature, believe before obtaining to acoustics
Number transmission flight time (step 500, step 510) and reversed acoustic signal transmission flight time (step 530, step
540) velocity of sound, and in the case where not influencing gas velocity is obtained using these flight time according to following equation formula.
Determined by the following equation similar for the equation of forward direction or downstream direction with being set forth above from energy converter/
Transceiver C is to energy converter/transceiver B reversed flight time:
The forward direction flight time is added with the reversed flight time according to following equation:
In view of velocity of sound c duplicate ratio airflow rate u it is square much bigger, party's formula is simplified to:
Wherein:
tBCBe from first transceiver/energy converter B to second transceiver/flight time of energy converter C；
tCBBe from second transceiver/energy converter C to first transceiver/flight time of energy converter B；
C is the velocity of sound for temperature and gas constant in air-flow；
For along the unit vector in the first sound ray path；And
It is the velocity vectors in air-flow.
The velocity of sound c determined in the step 550 of Figure 11 is then used to adjusting pin to the downstream of the velocity of sound in step 560
Flight time.Corrected downstream time of flight data is used to determine air-flow absolute speed in step 570.Along flight
In the case that the path temperature T of line is unknown, in step 550 determine same velocity of sound c in certain embodiments of the present invention by
For utilizing previously described constant entropy velocity of sound relationship c (x, y, z)=(γ .R.T)1/2Determine T, this is because γ, R and c (x,
Y, z) it is known.To determine similar mode with previously described path rate, once from each receiver/transmitter list
All path temperature T of member back and forth are it is known that then will be present into three-dimensional 64 (assuming that the case where illustrative 8 sensors) etc.
Warm line.Then, using known 3D chromatography imaging technique, three dimensional temperature distribution is mapped.
Advantageously, active acoustics temperature measurement and speed measurement carry out simultaneously in real time, to map gas flow temperature (3D
The 2D mapping of mapping or alternatively Fig. 9) and 3D airflow rate (Fig. 8).Execute simultaneously rate and temperature measurement it is exemplary
Acoustic signal transmission and receive timing be by transceiver/energy converter in the first array plane (for example, ZⅠThe 32A at place)
To emit acoustic signal.Pair in the case where being measured using 3D temperature, in axially spaced the second opposite plane
The transceiver for the transversal orientation answered/energy converter (e.g., ZⅡThe 34B to 34H at place) signal is received for rate processing and/or temperature
Degree processing.Remaining transmitting-receiving in the case where the measurement of 2D temperature is used only, in transceiver/energy converter in the first array plane
Device/energy converter (e.g., ZⅠThe 32B to 32H at place) signal is received for Temperature Treatment.As previously pointed out, it sends and connects
Receipts process can also be accelerated by using to each transceiver/energy converter using unique signal emission mode.In the presence of with make
Associated tradeoff is measured with 2D or 3D temperature.Using 3D temperature measurement technology, temperature and rate diagram it is accurate
It may not be most desired for spending in the case where gas velocity is 0.3 Mach or more, this is because in following equation
Shown in approximation may be in those speed ranges since there is no independently determining temperature reference value
It is less accurate.However, it is possible to using a pair of axially spaced 2D acoustic signal group and pass through corresponding 2D time-of-flight signals group
Determining two individual acoustics hygrogram determines independent temperature T a reference value.2D hygrogram is interpolated in turn to create body
Product hygrogram.The volume diagram will be used to provide for temperature value T, temperature value T in constant entropy velocity of sound equation with known gas
Constant R and specific heat ratio γ be used to obtain velocity of sound c together.The velocity of sound is used subsequently to obtain velocity vectors u (x, y, z).Once obtaining
Velocity vectors, so that it may mapping rates component, to eliminate in the previously described 3D rate and temperature map method to solid
The limitation of gas velocity of some lower than 0.3 Mach.
Utilize the implementation of the system and method for the array with usually used acoustic sensor described herein
The burner active flow rate or rate/temperature monitoring that mode carries out be considered as and known rate and temperature monitoring system
Compared to providing the response of faster rate and temperature change.Embodiment according to the present invention, usually used, reliable sound
Learn the battle array of sensors/transducers, one array of sensor-transmitter or individually discrete acoustic sensor and transmitter pair
Column can be placed in combustion flows path and can be monitored under the conditions of field with provide active, it is real-time while
Rate and temperature data and abnormality detection, these monitorings all to the combustion power generation equipment of such as industry gas turbine etc and
It controls useful.
Mapping parameters distribution
Parameter Map in two dimension or three-dimensional space serves many purposes in mechanical design, diagnosis and controlling party face.For example,
The temperature or rate diagram in the region of gas path are useful in the aspect of performance of diagnosis and precise measurement gas-turbine unit.
The legend such as can be the hygrogram near burner flame or can be the turbine inlet temperature left in the region of burner
Degree figure.Simple hygrogram is created currently with the electric thermo-couple temperature rake and temperature sensor that are mounted on first row blade,
To obtain the measurement that can be fitted rough linear temperature profile.Those short-term, intrusive methods are provided based on sensor
The rough profile of position, but without providing the space analysis figure of temperature in real time, the space analysis figure that can use temperature comes
Control gas turbine understands Temperature Distribution during the design verification process of new engine.
Presently described be for in the region of gas-turbine unit send and received acoustic signal or other
The technology that signal is utilized.Many flow regions of gas-turbine unit may be in the use of presently described technology
It is interested, and several exemplary areas carry out in the schematic diagram of gas-turbine unit 1200 shown in Figure 12
Describe.Can use described technology and using the acoustic sensor 1212 that is circumferentially arranged of plane domain around entrance come
Create inlet temperature Figure 121 1 of gas turbine inlet 1210.Burner temperature Figure 122 1 can be created to show burner 1220
Region in Temperature Distribution.According to interested region, sensor 1222 can pass around main burner flame zone or whirlpool
Take turns the horizontal layout of entrance (burner outlet).The information from sensor 1232 be can use to be constructed through turbine diffuser
The three-dimensional rate diagram 1231 of 1230 air-flow, multiple flat sites of the sensor 1232 in diffuser are circumferentially arranged.It can
To create the Temperature Distribution in 2 dimensional region of the delivery temperature Figure 124 1 to show turbine exhaust portion 1240 using sensor 1242.
Those skilled in the art will recognize that described technology can be arranged with other sensors and other gas-turbine units
Region executes the useful Parameter Map to generate other.
The advanced method of tomography principle be used to obtain space solution in real time using dozens of individual signal path
Analysis figure.As described above, sensor can be acoustic sensor, and the velocity of sound information about each path is processed to estimate to be somebody's turn to do
Mean temperature in path length.The expression containing mean temperature information in each path in each time interval, path
The spatial distribution of the temperature at measurement moment is mapped in a manner of tomography, and then in subsequent time of measuring by more
Newly.Information from resulting hygrogram can be used in engine control algolithm or the peace to keep engine to run
Full property and low emissions levels.
In embodiment as discussed above and in embodiment as shown in Figure 13, transmitter and sensor
1310 are circumferentially distributed around the cross section of the hot gas path of one or more turbine zones 1305.In some embodiments
In, sensor and receiver can be arranged on acoustic transceiver (the transmitter/receiver group in the plane of burner
Close), wherein those transceivers will send and capture in real time acoustic signal.Although the disclosure is referring to acoustics detection technology to biography
Sensor and receiver are discussed, but it will be appreciated by those skilled in the art that these sensors and receiver can be with
It alternatively uses based on the tunable diode laser absorption spectroscopy method of laser or another measuring technique and determines in burner
The mean temperature along line route.In the case where acoustic transceiver, transmitted signal, should for determining bulk sound velocity
Bulk sound velocity is for estimating mean temperature.
Several skill in the case where the tunable diode laser absorption spectroscopy method based on laser, for temperature measurement
Art is feasible.The mean temperature in path can be measured by following manner: while making laser inswept absorption spectrum, be visited
Survey two different Absorption Lines of same composition (species).It is produced by the gas by the plane in specific IR wavelength band
Raw laser absorption and concentration of component and temperature proportional, and can be solved to provide the average path temperature along each line
Degree.Alternatively, the full width at half maximum (FWHM) (FWHM) of the Absorption Line detected can be related with the doppler linewidth degree of component.It is not carrying on the back
In the case where from the scope of the present disclosure, other temperature measurement technologies based on laser or other temperature measurement skills can be used
Art.
In the case where temperature map, tomography mapping block 1315 is in each time interval being sampled to temperature
By multiple average path temperature transitions at hygrogram 1320.Two dimension or three-dimensional figure may include the isothermal of higher spatial resolution
Line, and provide the information more more valuable than individual average path Temperature estimate value, with illustrate engine health situation with
And the input for engine control algolithm.Hygrogram 1320 is sent to hair together with the combustion quality information 1325 obtained
Motivation control unit 1330, control unit of engine 1330 utilize the information to control burner and/or gas-turbine unit.
It is described herein although being described referring to hygrogram is constructed according to average path Temperature estimate value
Technology can be also used for constructing other two dimensions or three-dimensional figure according to path average value.For example, along the road of transmitters and receivers
The Mean Speed of the estimation of diameter can be used for the two dimension or three-dimensional figure using similar method construct local velocity.
Described herein is for according to one group of path average line mapping parameters in a certain region and acquisition and parameter
The several different technologies of relevant spatial information.These technologies include polynomial approximation method, Basis Function Method and grid optimization method.
Every kind of technology in these technologies will be successively described below.Although several descriptions in these descriptions are related to gas
The illustrative embodiments that stream temperature measures, but those skilled in the art will recognize that, described technology is on edge
Be suitable for mapping other parameters in the available situation of average value of linear path.
Approximation by polynomi-als technology: multiple average path temperature transitions are by completion at a kind of mode of the task of hygrogram:
By approximation by polynomi-als along the temperature profile of each path, and then by as shown in the flow chart 1500 of Figure 15
Iterative process is adjusted so as to minimize the error each polynomial parameter.For this purpose, in operating 1510 (Figure 15), often
A path --- path 1405 as shown in fig. 14 a --- has been initially assigned following temperature funtions: the temperature funtion includes
Scale factor and the mean temperature for reflecting the estimation along the path.In bilinearity profile 1400, temperature from endpoint 1415,
1420 (that is, sending points and receiving point at locular wall) linearly increase, to form vertex 1425, to generate transversal with tent
Profile as noodles.Initial maximum temperature appears in the apex, and minimum (wall) temperature appearance is located at either end.From hair
The distance 1430 on sending end point 1415 to vertex 1425 is determined by midpoint scale parameter.Midpoint scale parameter can initially be defaulted
Ground is set to the 50% of path length.
Apex height 1410 limits the initial maximum temperature along path 1405 at vertex 1425.Initially, apex height
Scale factor can be set to twice of value of average path temperature.
Endpoint 1415,1420 is it may be provided that at being constant and being kept and algorithm relevant to wall temperature variable
In constant level.Wall temperature variable can select in several ways.In one example, fixed value is manually inputted.
In another example, the percentage of average path temperature or minimal path temperature has been used.In other embodiments, such as high
The real sensor of warm galvanic couple etc is for wall temperature signal to be directly inputted in algorithm.
It executes from sending point 1415 (wall temperature) Xiang Zhongdian 1425 (scale factor that the path temperature measured iterates to calculate)
And it is back to the bilinear integral form of receiving point 1420 (wall temperature).
Then, in operation 1520, estimated path profile 1400 is drawn into the flat site for indicating room 1401
Two-dimensional grid, as shown in Figure 14 B.For each path, such as illustrative second path 1450, the process is repeated.Work as institute
When some temperature are all drawn on grid, which includes the rarefaction representation of hygrogram.Therefore, exist on grid and be located at road
The missing point in open area (open area) between diameter.In these open areas, such as Bessel function etc is used
Curve-smoothing technique this group of known point is converted into the polynomial approximation of the actual temperature curve at the discrete point on grid
Value.After grid is smoothed, line integral is executed along line route in operation 1530, and by the line in operation 1540
It integrates and is compared with the data measured.The comparison result is used in box 1570 adjustment proportional factor with for next time
Iteration, so that minimizing the error between the temperature of the temperature and estimation that measure.It can be according to 1550 iteration of decision
Process 3 times to 20 times, to generate the surface (surface) compared with the original average path temperature measured with minimal error.
When error is lower than preset maximum value, iteration ends are in operation 1560.Although without isollaothermic chart generated
Absolute error or precision specific requirement, but average path error amount can be calculated, be set with being provided for any given figure
Believe factor.For the canonical system of normal operating, in the range of average path error will be distributed over from 0 to 3%-4%.If most
Mapped plan and physical agent have been selected goodly, this can be used for point-device space diagram according to path averaged temperature information.
Basic function technology: for being using base letter by another technology that multiple average path temperature transitions are two-dimensional temperature map
Number.In general, each continuous function in function space can be indicated by the linear combination of basic function.It is presently described,
In the flow chart 1700 of Figure 17 in discribed technology, hygrogram is linear by the two dimensional basis functions that are obtained according to thermocouple measurement
Combination is to indicate.
Operated as shown in 1710, using the statistical method of such as principal component analysis (PCA) etc, surveyed from electric thermo-couple temperature
Amount or the large database concept of other parameters measurement extract two dimensional basis functions.For based on the fixed value that is manually entered or based on measuring
The two dimensional basis functions of wall temperature, boundary condition are fixed/constant.The technology acquires the weight for basic function, the power
Make minimizing the error for the flight time measured again.In embodiments, weight is iteratively acquired.
In one embodiment, there are the K two dimensional basis functions obtained by thermocouple measurement.There is also I acoustics roads
Diameter i and mean temperature ti, mean temperature is estimated according to along each flight time measurement of acoustic path.For each
Basic function and each path, path temperature are sampled (operation 1720) into the vector of the length D along path.For each path
I, probe temperature are collected into the matrix X of D × Ki, as shown in the matrix 1600 of Figure 16, for single path, Figure 16 shows use
In six basic function K1To K6Six temperature profiles, each basic function is in five position D1To D5Place is sampled.For example,
For basic function K shown in matrix 16001, show five sample point D along path1To five temperature samples of D5.It is right
Each path in other paths, establishes similar matrix.Target is when acquiring (operation 1730) most preferably to represent by flight
Between the combination of the basic function of mean temperature that measures.The weighted array of basic function is provided by weight vector a, can be in the hope of are as follows:
Lattice optimization techniques: in the embodiment using acoustic signal, the average path temperature of estimation can use figure
Lattice optimization techniques shown in 19 flow chart 1900 are converted into two-dimensional temperature map, in lattice optimization techniques, two dimension
Figure is divided into multiple meshings (operation 1910), meshing 1820 as shown in Figure 18.Target is to each grid
Value (temperature or rate) in part is estimated.Meshing is limited to the area delimited by the horizontal line of grid and vertical line
Domain.The speed of acoustic signal in each meshing, which is assumed that into, to be consistent.
In operation 1920, the distance covered when through each meshing by each acoustic path is counted first
It calculates.In the example shown in Figure 18, determine in meshing by path 1831, path 1833, path 1835 and path
1837 distances passed through.By each path total flight time and by each path pass through each meshing passed through away from
From being known, therefore it can be passed through along propagated by each meshing the time it takes and solve following equation
Group calculates:
Wherein, n is the label in path, and m is the label of meshing, and t is the flight time of given path, and x is each net
The inverse with the velocity of sound in the meshing of lattice partCorresponding coefficient, and d is to pass through each grid by path n
The distance that part m is passed through.
The coefficient of meshing corresponding with boundary is applied with downstream condition,
xw=c
Wherein, w corresponds to the label of the meshing of wall and c is the constant obtained by wall temperature.
In order to reduce search space and solving result is restricted in acceptable range, the upper limit of the coefficient is under
Limit is applied based on physical reality (physical reality).For example, the temperature of each meshing can be constrained to height
In room temperature and it is lower than 1000 DEG C of value.
The quantity of meshing to be solved can substantially exceed the quantity of path equation formula, be enable to a large amount of
Solution.In this case, it is applied with the additional optimization mark as minimized the difference between the velocity of sound in adjacent mesh part
Standard is to obtain the smooth figure closer to actual conditions.
After the acoustic velocity value for calculating each meshing (operation 1930), the temperature value of meshing is estimated, and can
To establish hygrogram (operation 1940) using these temperature values.
In embodiments, above-mentioned technology can be applied to control gas-turbine unit using temperature data.
Once calculating two-dimensional temperature map, which can be used to calculate in real time the information useful to control engine.Example
Such as, referring to Fig.1 3, if combustion system is shaped combustion system or circular pipe type combustion system, tomography mapping block 1315
Can in volume mean temperature (mean temperature of figure), plane Temperature Distribution (according to grade of fit function or according to profile) and
Temperature difference between different burner inner liners is calculated.The information is then provided to control unit of engine 1330, engine
Control unit 1330 intelligently programmed with control engine parameter with realize optimal engine performance (safety, performance and
Emission).
As described earlier, transceiver/energy converter 32A to 32H and transceiver/energy converter 34A to 34H (see Fig. 5) hair
Send and receive the acoustic signal for limiting acoustic path.It is subsequently used to generate temperature along the flight time measurement of corresponding acoustic path
Degree figure, hygrogram 1320 as shown in Figure 13.Each acoustic signal by transceiver/energy converter 32A to 32H and transceiver/
Energy converter 34A to 34H is sent and is received by waveguide associated with transceiver/energy converter.
Referring to Figure 20, the multiple acoustic paths 2000 for propagating across the measurement space 2010 of hot gas flow path 2020 are shown
Exemplary sectional view.For purposes of illustration, hot gas flow path 2020 is located in burner 20, it will be understood however, that
Hot gas flow path 2020 may be located in turbine diffuser 1230 (see Figure 12) or exhaust pipe.Figure 20 depicts multiple transmitting-receivings
Device/energy converter (that is, transceiver), each transceiver/energy converter all have waveguide, for example, transceiver 2040A to 2040F distinguishes
With corresponding waveguide 2030A to 2030F.Transceiver 2040A to 2040F is only to transceiver 2040A to the sky between 2040F
Between, i.e. measure space 2010 in air temperature and current amount measure.However, not to the entity for limiting hot gas flow path 2020
The temperature of boundary measures.In addition, also not measured to the temperature in waveguide 2030A to 2030F.In embodiment
In, entity boundary can be the wall 2050 of burner 20.
In order to generate hygrogram, it is assumed that or selected temperature be used for wall 2050 and waveguide 2030A to 2030F.Herein
Inventor it has been found that the temperature of wall 2050 and the temperature of waveguide 2030A to 2030F are to Temperature Distribution indicated by hygrogram
The important parameter being had an impact with temperature value.However, temperature that is used selected or assuming is often mistake, cause to be used for
The inaccurate hygrogram for the thermal current not characterized previously.
Hygrogram includes the temperature information to be formed near the wall of hot gas flow path.Embodiment according to the present invention is based on
Temperature near the wall 2050 as indicated by initial temperature figure calculates waveguide temperature.In embodiments, wall temperature is established
Linear relationship between angle value and waveguide temperature, it will be appreciated that non-linear relation can also be used.Referring to Figure 21, wall
2050 boundary part 2060 is divided into multiple virtual 2070 Α of boundary part to 2070 Η and (shows eight exemplary borders
Part), the label of boundary part is consequently formed.Each boundary part 2070A to 2070H waveguide corresponding with respectively including
The correspondence transceiver 2040A to 2040H of 2030A to 2030H is associated so that waveguide 2030A to 2030H be positioned to it is corresponding
Boundary part 2070A to 2070H is adjacent or relatively close.The temperature of each waveguide 2030A to 2030H according to equation (1) by
The temperature of its associated 2070 Α of boundary part to 2070 Η determines:
TempAtWaveGuide (tr_i)=
0.75x estimated_wall_value(matching_boundary_portion)+30K (1)
Wherein, " tr_i " corresponds to energy converter associated with boundary part 2070A to 2070H/receiver 2040A extremely
The number of 2040H, " tempAtWaveGuide (tr_i) " correspond to the waveguide 2030A to 2030H of energy converter number " tr_i "
Temperature, and " K " is Kelvin temperature scale, it will be appreciated that other temperature scales can also be used."estimated_
Wall_value (matching_boundary_portion) " is boundary part 2070A to 2070H associated with energy converter
Estimation temperature.This makes it possible to calculate the temperature of each boundary part 2070A to 2070H, and hereby based on every
A boundary part 2070A to 2070H calculates corresponding waveguide temperature, to obtain multiple waveguide temperatures as shown in Figure 24.
As will be described, equation (1) can be used for calculating initial waveguide temperature.
In another embodiment, wall 2050 is not divided, as shown in Figure 22, and extremely for each waveguide 2030A
2030H assumes consistent temperature value.The temperature of complete boundary part 2080 is calculated.All waveguide 2030A are extremely
The temperature of 2030H is all provided by equation (2):
TempAtWaveGuide=0.75xmean_estimated_wall_value+30K (2)
Wherein, " tempAtWaveGuide " is the temperature of all waveguide 2030A to 2030H, " mean_estimated_wall_
Value " is the estimation mean temperature of complete boundary part 2080, and " K " is Kelvin temperature scale, it will be appreciated that
Other temperature scales can also be used.
Referring back to Figure 20, the total flight time of acoustic signal is that acoustic signal is propagated across waveguide 2030A to 2030H
Time quantum and the acoustic signal pass through the time quantum that measurement space 2010 is propagated and.It subtracts from total flight time across waveguide
2030A to 2030H propagates the time it takes, and remaining time is subsequently used in generation hygrogram.Waveguide temperature is to influence
The important parameter of the flight time of acoustic signal.Make for example, calculating the waveguide temperature updated via equation (1) in measurement sky
Between the corresponding variation of the time it takes is propagated in 2010.This causes remapping for hygrogram again.Once generating new temperature
Figure, new wall temperature is obtained according to new hygrogram, and new wall temperature is subsequently used to calculate newly using equation (1) again
Or the waveguide temperature of estimation.It should be understood that equation (2) can be used to replace equation (1) to update waveguide temperature.
If the difference between the initial waveguide temperature calculated before the waveguide temperature of estimation and the waveguide temperature closely estimated
It is bigger than predetermined temperature difference, i.e. bigger than temperature difference threshold value, then continuous updating waveguide temperature, and generate new hygrogram.If estimated
Difference between the waveguide temperature of meter and initial waveguide temperature is less than or equal to temperature difference threshold value, then the temperature and its phase of boundary part
The temperature convergence of associated waveguide and process stopping.
Referring to Figure 23, flow chart 2000 is shown, it illustrates embodiment according to the present invention for determining waveguide
The method of temperature.When this method starts, in step 2105, the initial waveguide temperature of the initially use hypothesis for each waveguide
Degree.In embodiments, in step 2105, initial waveguide temperature is set to room temperature, it will be appreciated that can also make
With other temperature.In step 2100, total flight time is the time quantum that acoustic signal passes through that waveguide 2030A to 2030H is propagated
With the acoustic signal pass through measurement space 2010 propagate time quantum and.In step 2110, wave is subtracted from total flight time
The propagation time is led, to provide the propagation time across measurement space 2010.In step 2120, based on across measurement space 2010
Propagation time calculate hygrogram.Next, obtaining wall temperature according to hygrogram in step 2130.In step 2140,
The waveguide temperature of the estimation of each waveguide 2030A to 2030H is calculated based on equation (3):
EstWaveGuide (tr_i)=
0.75x estimated_wall_value(matching_boundary_portion)+30K (3)
Wherein, " tr_i " corresponds to energy converter associated with boundary part 2070A to 2070H/receiver 2040A extremely
The number of 2040H, " estWaveGuide (tr_i) " correspond to the waveguide 2030A of energy converter number " tr_i " to 2030H's
Temperature, and " K " is Kelvin temperature scale, it will be appreciated that other temperature scales can also be used."estimated_wall_
Value (matching_boundary_portion) " is the estimation of boundary part 2070A to 2070H associated with energy converter
Temperature.
In step 2150, if the waveguide of the estimation of each waveguide 2030A to 2030H obtained according to equation (3)
Temperature (that is, " estWaveGuide (tr_i) ") and assume initial waveguide temperature or with the wave with the estimation being previously calculated out
The difference led between the equal initial waveguide temperature of temperature is bigger than temperature difference threshold value, then in step 2155, by initial waveguide temperature
It is set equal to the waveguide temperature (" estWaveGuide (tr_i) ") of the estimation of each waveguide 2030A to 2030H.Therefore, often
The initial waveguide temperature of a waveguide and the waveguide temperature of estimation are present in the different moments in this method.This method is subsequently returned to
Step 2110 and step 2120,2130 and 2140 are repeated, to execute another iteration of this method and obtain each waveguide
The waveguide temperature (" estWaveGuide (tr_i) ") of the new estimation of 2030A to 2030H.
If the condition in step 2150 is not met for, that is, the waveguide temperature of estimation is obtained by equation (3)
Estimation waveguide temperature and initial waveguide temperature between difference be less than or equal to temperature difference threshold value, the then boundary part of wall 2050
2070A is to the temperature convergence of the temperature of 2070H and its associated waveguide 2030A to 2030H and the process stops.This is also
Show wall temperature and waveguide temperature is relative constant.In embodiments, temperature difference threshold value is about 5 DEG C.This method it is each
Aspect may be performed that for previously described tomography mapping block 1315, computer system or other computing devices
In algorithm or computer program.
Referring to Figure 24, curve graph 2160 is shown, which shows showing for each waveguide 2030A to 2030F
Example property waveguide temperature curve 2170.Each temperature curve 2170 obtains during the iteration of this method.It can from curve graph 2160
To observe, as the number of iterations of this method increases thus to improve the precision of indicated waveguide temperature, Mei Gebo
It leads temperature and starts convergence (that is, as described earlier, the difference between the waveguide temperature of estimation and initial waveguide temperature becomes to get over
Come smaller).In this example, waveguide temperature after about 30 iteration in the region of curve graph 2,160 2180 restrain with
Thereby indicate that accurate temperature.In embodiments, fast mapping algorithm can be used, which is measuring every time
In iteration it is multiple, to allow waveguide temperature to restrain, and have no substantial effect on the real-time performance of whole system 29.This is in primary wave
It can be realized the faster convergence of waveguide temperature in the case where leading between temperature and the waveguide temperature of estimation there are larger difference,
And make it possible to generate approximate temperature figure more quickly.Once the as low as selected threshold value of waveguide temperature subtractive, so that it may more smart
Really solve hygrogram.
Figure 25 to Figure 30 respectively depicts illustrative hygrogram 2190,2200,2210,2220,2230 and 2240, this
The temperature that a little temperature show waveguide is restrained as the number of iterations increases.Hygrogram 2190 to 2240 includes temperature region
2250,2260,2270,2280, the arrangement and instruction temperature of these temperature regions change as the number of iterations increases, thus change
The Temperature Distribution of covert associated hygrogram.Initial temperature Figure 21 90 is shown in FIG. 25, in initial temperature Figure 21 90, initially
The waveguide temperature that respectively waveguide 2030A to 2030F estimates is 35 DEG C, 38 DEG C, 36 DEG C, 30 DEG C, 30 DEG C, 31 DEG C.Figure 26 extremely schemes
29 show the iteration of this method, wherein in every width figure, waveguide temperature is updated and hygrogram correspondingly changes.Figure
30 depict final hygrogram 2240, wherein the difference between the waveguide temperature of estimation and initial waveguide temperature is less than or equal to
Temperature difference threshold value, that is, as described earlier, temperature convergence.In Figure 25 into Figure 30, execute additional iteration (up to 45 times
Iteration), to show stable algorithmic statement.
Only there are significant changes, the estimation to boundary conditions and waveguide situation is repeated to limit calculating cost
With the influence to whole system 29.That is, once boundary conditions and the convergence of waveguide situation, the algorithm are maintained for the boundary of tracking variation
Situation is to keep the precision of total figure.In practice, once boundary conditions and waveguide temperature convergence, just calculate complete hygrogram.
In embodiments, the study historical record of the relationship between waveguide temperature and hygrogram can be used to improve to waveguide temperature
Estimation.For example, the waveguide temperature and hygrogram of the test engine from similar gas turbine or with similar temperature characterisitic
Between relationship record or data can be used to improve estimation to waveguide temperature.In addition it is possible to use according to previous temperature
The waveguide temperature for the estimation that mapping result obtains is spent to improve the convergence rate of waveguide temperature.In addition, to possible mapping result
Constraint can be used to improve the accuracy and speed of temperature map, for example to the constraint of possible mapping result are as follows: limitation is such as
The temperature range of the temperature range of waveguide etc or other temperature ranges, so that only allowing foundation drawing and linear group of other figures
It closes.
The present invention provides a kind of methods for automatically determining boundary and waveguide situation, and extend mapping to use
Boundary and waveguide situation.Particularly, calculating is iterated to obtain accurate temperature to waveguide temperature and boundary temperature in real time
Figure, without carrying out actual measurement (that is, not needing by using temperature-sensing device or spy to waveguide temperature and boundary temperature
Device is surveyed to measure temperature).The present invention reduces to being waveguide and wall and other area equipment instruments to obtain boundary conditions
Demand.In addition, the present invention improves the temperature of thermal current, the precision of rate and mass flow measurement.
Although the different embodiments for combining teachings of the present invention are shown and are described in detail herein,
But those skilled in the art can also easily design many other different embodiment party for still combining these teachings
Formula.The present invention its application aspect be not limited to propose in specification and the construction of component shown in the accompanying drawings and showing for arrangement
The details of example property embodiment.However, the various aspects of the invention being more fully described herein can be adapted for it is following its
His example: in these examples, the profile diagram of the value in region based on the average value along the linear path for passing through the region come
It determines.The present invention can have other embodiments and can practice or be implemented in different ways in different method.Though
So acoustic sensor and laser sensor are discussed, it is also possible to use other measuring techniques.Additionally, it should be appreciated that
, wording used herein and term are for purposes of illustration, without that should be viewed as a limitation.It is used herein
"include", "comprise" or " having " and its variant mean to include the project behind enumerated and its equivalent and sundry item.
Unless otherwise specified or limited, otherwise term " installation ", " connection ", " bearing " and " connection " and its variant are all broadly made
With and including installation, connection, bearing and connection directly or indirectly.In addition, " connection " and " connection " is not limited to physics
Or mechanical connection or connection.
Claims (20)
1. a kind of method for determining the waveguide temperature at least one waveguide being used in combination with transceiver, the transceiver produce
Raw acoustic signal, the acoustic signal pass through the measurement spatial in the hot gas flow path limited by wall, which comprises
Calculate the total flight time of the acoustic signal, wherein the total flight time includes the biography across the measurement space
Propagation time between sowing time and across the waveguide；
The waveguide propagation time is subtracted, from the total flight time to obtain measurement space propagation time；
Hygrogram is calculated based on the measurement space propagation time；
The wall temperature of estimation is obtained according to the hygrogram；And
Wall temperature based on the estimation calculates the waveguide temperature of estimation, wherein when determining the waveguide temperature of the estimation, no
Use temperature-sensing device.
2. each boundary part is equal according to the method described in claim 1, wherein, the wall is divided into multiple boundary parts
Associated transceiver and adjacent waveguide, wherein the temperature of each boundary part is used to calculate the wave of corresponding estimation
Lead temperature.
3. according to the method described in claim 2, wherein, the linear phase of wall temperature of the waveguide temperature of the estimation and the estimation
It closes.
4. according to the method described in claim 1, wherein, the difference between the waveguide temperature and initial waveguide temperature of the estimation
When greater than temperature difference threshold value, the initial waveguide temperature is set equal to the waveguide temperature of the estimation, and is iteratively held
Row the method provides the iterative estimate of waveguide temperature hereby based on the hygrogram of estimation.
5. according to the method described in claim 4, wherein, using fast mapping algorithm, the fast mapping algorithm is being surveyed every time
Equal iteration is multiple in amount, and the real-time performance of associated system is had no substantial effect on can be realized waveguide temperature convergence.
6. according to the method described in claim 4, wherein, the temperature difference threshold value is about 5 DEG C.
7. a kind of method for determining the waveguide temperature in gas turbine, the described method comprises the following steps:
(a) at least one transceiver for generating acoustic signal is provided, the acoustic signal is passed through by the wall in the gas turbine
Measurement spatial in the hot gas flow path of restriction, wherein at least one described transceiver includes waveguide；
(b) total flight time of the acoustic signal is calculated, wherein the total flight time includes across the measurement space
Propagation time and propagation time across the waveguide；
(c) the waveguide propagation time is subtracted from the total flight time to obtain measurement space propagation time；
(d) hygrogram is calculated based on the measurement space propagation time；
(e) wall temperature of estimation is obtained according to the hygrogram；
(f) waveguide temperature of estimation is calculated based on the wall temperature of the estimation, wherein when the estimation waveguide temperature and just
When difference between beginning waveguide temperature is greater than temperature difference threshold value, step (c) is repeated to step (e), wherein when the waveguide of the estimation
When difference between temperature and initial waveguide temperature is less than or equal to the temperature difference threshold value, convergent waveguide temperature is determined, and
Wherein, when determining the waveguide temperature of the estimation, temperature-sensing device is not used；
(g) estimation to waveguide temperature is improved using the study historical record of the relationship between waveguide temperature and hygrogram.
8. the method according to claim 7, wherein the wall is divided into multiple boundary parts, and each boundary part is equal
Associated transceiver and adjacent waveguide, wherein the temperature of each boundary part be used to calculate corresponding estimation
Waveguide temperature.
9. according to the method described in claim 8, wherein, the linear phase of wall temperature of the waveguide temperature of the estimation and the estimation
It closes.
10. 7 method according to claim, wherein when the estimation waveguide temperature and the initial waveguide temperature it
Between difference be greater than the temperature difference threshold value when, the initial waveguide temperature is set equal to the waveguide temperature of the estimation, and
And it is iteratively performed the method, the iterative estimate of waveguide temperature is provided hereby based on the hygrogram of estimation.
11. method according to claim 10, wherein use fast mapping algorithm, the fast mapping algorithm is measuring every time
In iteration it is multiple, have no substantial effect on the real-time performance of associated system can be realized waveguide temperature convergence.
12. according to the method described in claim 7, wherein, the temperature difference threshold value is about 5 DEG C.
13. a kind of method for determining the waveguide temperature at least one waveguide being used in combination with transceiver, the transceiver
Acoustic signal is generated, the acoustic signal passes through the measurement spatial in the hot gas flow path limited by wall, the method packet
Include following steps:
(a) wall is divided into multiple boundary parts, wherein each boundary part is associated with transceiver and waveguide；
(b) total flight time of the acoustic signal is calculated, wherein the total flight time includes across the measurement space
Propagation time and propagation time across the waveguide；
(c) the waveguide propagation time is subtracted from the total flight time to obtain measurement space propagation time；
(d) hygrogram is calculated based on the measurement space propagation time；
(e) temperature of the estimation of each boundary part is obtained according to the hygrogram；And
(f) waveguide temperature of the corresponding estimation of temperature computation of the estimation based on each boundary part, wherein estimate described in the determination
When the waveguide temperature of meter, temperature-sensing device is not used.
14. the method according to claim 13, wherein the estimation of the waveguide temperature of the estimation and corresponding boundary part
Temperature linearity it is related.
15. according to the method for claim 13, wherein when between the waveguide temperature and initial waveguide temperature of the estimation
When difference is greater than temperature difference threshold value, the initial waveguide temperature is set equal to the waveguide temperature of the estimation, and iteratively
The method is executed, provides the iterative estimate of waveguide temperature hereby based on the hygrogram of estimation.
16. according to the method for claim 15, wherein use fast mapping algorithm, the fast mapping algorithm is each
Equal iteration is multiple in measurement, and the real-time performance of associated system is had no substantial effect on can be realized waveguide temperature convergence.
17. according to the method for claim 15, wherein the temperature difference threshold value is about 5 DEG C.
18. the method according to claim 13, wherein the waveguide temperature of the estimation is obtained and restraining waveguide temperature
, and the waveguide temperature of the estimation previously obtained is used to improve the convergence rate of waveguide temperature.
19. according to the method for claim 18, wherein received after step (c) to step (f) iteration about 30 times
It holds back.
20. according to the method for claim 13, the constraint that the method also includes being limited the temperature range of waveguide.
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| US14/682,393 US10041859B2 (en) | 2014-03-13 | 2015-04-09 | Parameter distribution mapping in a gas turbine engine |
| US14/682,393 | 2015-04-09 | ||
| PCT/US2015/026784 WO2015164313A1 (en) | 2014-04-23 | 2015-04-21 | Method for determining waveguide temperature for acoustic transceiver used in a gas turbine engine |
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| CN201580021152.2A Expired - Fee Related CN106233110B (en) | 2014-04-23 | 2015-04-22 | Method for optimizing base points used in a temperature map of a turbine hot gas flow path by determining intersection points of acoustic signals |
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| US9709448B2 (en) | 2013-12-18 | 2017-07-18 | Siemens Energy, Inc. | Active measurement of gas flow temperature, including in gas turbine combustors |
| US9752959B2 (en) | 2014-03-13 | 2017-09-05 | Siemens Energy, Inc. | Nonintrusive transceiver and method for characterizing temperature and velocity fields in a gas turbine combustor |
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- 2015-04-21 CN CN201580021136.3A patent/CN106233109B/en not_active Expired - Fee Related
- 2015-04-22 DE DE112015001963.4T patent/DE112015001963T5/en not_active Withdrawn
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Also Published As
| Publication number | Publication date |
|---|---|
| WO2015164466A1 (en) | 2015-10-29 |
| DE112015001905T5 (en) | 2017-02-02 |
| DE112015001963T5 (en) | 2017-01-19 |
| WO2015164313A1 (en) | 2015-10-29 |
| CN106233110B (en) | 2020-06-16 |
| CN106233109A (en) | 2016-12-14 |
| CN106233110A (en) | 2016-12-14 |
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