GB2133877A - Generation of a signal dependent upon temperature of gas turbine rotor blades - Google Patents
Generation of a signal dependent upon temperature of gas turbine rotor blades Download PDFInfo
- Publication number
- GB2133877A GB2133877A GB08333670A GB8333670A GB2133877A GB 2133877 A GB2133877 A GB 2133877A GB 08333670 A GB08333670 A GB 08333670A GB 8333670 A GB8333670 A GB 8333670A GB 2133877 A GB2133877 A GB 2133877A
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- signal
- radiance
- temperature
- gas turbine
- turbine engine
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- 238000009499 grossing Methods 0.000 claims abstract description 9
- 239000000446 fuel Substances 0.000 claims description 22
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0022—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiation of moving bodies
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/02—Arrangement of sensing elements
- F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
- F01D17/085—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure to temperature
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0088—Radiation pyrometry, e.g. infrared or optical thermometry in turbines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/80—Calibration
- G01J5/808—Calibration using linearising circuits
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Spectroscopy & Molecular Physics (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Radiation Pyrometers (AREA)
Abstract
Apparatus for the generation of a monitor signal for use in the operation of a gas turbine engine, the monitor signal being dependent upon the temperatures of a stage of turbine rotor blades in the gas turbine engine, includes an optical radiation pyrometer (1) having an output signal (R0) which, ignoring radiant interference, is representative of the real-time average radiance of the hottest parts of an integer number of the turbine rotor blades, the integer number being a fraction of the total number of blades on the rotor. After analogue-to- digital-conversion in an ADC (3), subsequent processing is carried out by means of a filter function (9) for removal of radiant interference, a smoothing function (13) for reduction of fluctuations in radiance signal strength caused by variations in average radiance of neighbouring blades, a linearising function (17) for conversion to a temperature signal (T), and a comparison function (21) for production of a control signal ( DELTA ) by comparing the temperature signal (T) with a reference temperature signal (Tref) produced by a datum unit (23). <IMAGE>
Description
SPECIFICATION
Generation of signals dependent upon temperatures of gas turbine rotor blades
The present invention relates to apparatus capable of generating a monitor signal for use in operation of a gas turbine engine, said monitor signal being dependent upon the temperatures of a stage of turbine rotor blades in the gas turbine engine.
It is known to control fuel flow to the combustion chambers of a gas turbine engine in partial dependence upon a pyrometer-derived control signal bearing a relationship to the temperature of the high pressure stage turbine rotor blades, but problems have been experienced in designing pyrometer-linked apparatus which can provide a fuel control system with a signal which (insofar as the response time of the control system is concerned) is congruous with changes in the instantaneous average temperature of all the rotor blades in the stage, even during periods when the rotor blade temperatures are changing rapidly, as for example when the engine is being rapidly accelerated or decelerated.Such a "real time" signal is particularly required for fuel control systems which exercise continuously active control of fuel flow in accordance with blade temperature rather than occasional control merely to avoid hazardous overheating of blades.
It is an object of the present invention to facilitate the provision of such a pyrometerderived signal.
The present invention provides apparatus for generating a monitor signal for use in the operation of a gas turbine engine, said monitor signal being dependent upon the temperatures of a stage of turbine rotor blades in the gas turbine engine, said apparatus including: optical radiation pyrometer means which in operation produces a radiance signal comprising a first component representative of the real-time average radiance of the hottest parts of an integer number of turbine rotor blades, and a second component due to transient interference from non-blade sources of radiation, said integer number being a fraction of the total number of blades on the rotor; and signal processing means adapted to derive said monitor signal from said radiance signal.
The real-time radiance signal is described as comprising two components because a further problem arises from the fact that the field of view of the optical radiation pyrometer is liable to be crossed at intervals by sources of radiation relating to the combustion process. These nonblade sources of radiation cause the basic bladeoriginating component of the radiance signal to be transiently over-lain by an "interference" component, making it unsuitable for direct use as a control signal.
Consequently, we prefer that the signal processing means includes signal filtering means adapted to filter out the second component of the radiance signal.
Depending upon the design characteristics of the engine and the turbine blades and also upon the magnitude of the above-mentioned integer number, the filtered radiance signal can be subject to fluctuations in strength due to differences in the individual average radiances of neighbouring blades on the rotor. This again might render the signal unsuitable as a control signal.
Accordingly the above-mentioned apparatus preferably further includes signal smoothing means adapted to reduce the amplitude of fluctuations in the strength of the first component of the radiance signal.
Preferably, the optical radiation pyrometer means comprises an optical radiation pyrometer according to the invention disclosed in our copending British patent application number 8330307, and the signal filtering means comprises signal processing means operating according to Claim 2 of our prior British patent number 1 590835.
Further aspects of the invention will become apparent from the following description and claims.
An embodiment of the invention will now be described by way of example only with reference to the accompanying drawing, which is block diagram showing the functional layout of digital electronic signal processing apparatus linked to an optical radiation pyrometer.
In the drawing, an optical radiation pyrometer 1 monitors the radiance of turbine rotor blades in a gas turbine engine (not shown) and delivers an amplified radiance signal R0 in analogue form on line 2 to an analogue-to-digital converter (ADC) 3 which is triggered at high frequency on line 5 to sample A0 and give a digital version comprising data word outputs RoI, Ro2 Rio3 . . etc at that frequency on line 7.
Signal A0 consists of two components, namely a basic blade radiance component and an intermittent interference component superimposed thereon. Filter function 9 moves the latter component and outputs a filtered radiance signal RF on line 11 comprising data words Asp1, RF2' AFs, etc which may fluctuate in value as explained later. They are consequently passed to a smoothing function 13 whose output A9 on line 15 is a stream of data words Rs1, Ras2, ....... etc representing blade radiance values acceptable for derivation of a control signal therefrom by subsequent means in the system.
If necessary, the smoothed radiance signal A9 is converted to a temperature signal T by linearising function 1 7 whose output of data words T1, T2, .... . etc on line 19 represents turbine blade temperature values. These are passed to a comparator function 21 which compares data words T1,T2,T3... etc with blade temperature reference value(s) Tref from a datum unit 23 and produces a control signal A by evaluating the difference between T and Trek, the signal A comprising data words A1, A2, . . . etc which are deviations from a null signal.
The apparatus will now be explained in more detail in the following sections (a) to (f).
(a) Radiation pyrometer
Data on turbine blade radiance is gathered by an optical radiation pyrometer operating at an infra-red wave-length. The radiation sensor element is a photo-diode, which receives radiation focussed onto it by a lens system. The optical arrangement is as disclosed in our copending patent application number 8330307, and consequently the strength of the signal from the photodiode is representative of the real-time (i.e. effectively instantaneous) average radiance of the hottest parts of an integer number of the turbine blades, plus any interference due to other sources of radiation within the field of view of the pyrometer. The integer number is not more than three because of the limitations inherent in the optical system and the turbine/pyrometer combination, i.e. the integer number is necessarily a fraction of the total number of blades on the rotor.
In fact, besides being representative of the average radiance of the hottest parts of an integer number of blades, the pyrometer's output signal A0 is at or quite near a true measure of the average radiance the hottest parts of all the blades on the rotor, apart from the interference mentioned earlier and also blade-to-blade variations in radiance which may be caused by the fact that some blade aerofoils may run hotter than others. The interference and the blade-toblade variations in radiance can cause fluctuations in the strength of signal A0 which can be removed by filtering and smoothing as mentioned later in order to produce a suitable control.Note that the magnitude of radiance signal fluctuations caused by variations in the average radiance of neighbouring blades depends upon the design characteristics of the engine and of its turbine and combustion systems in particular, and also upon the magnitude of the above-mentioned integer number. It may be that if the integer number is two or three and the engine's design characteristics are favourable, these fluctuations would be small enough to ignore and the smoothing function could be deleted from the apparatus.
(b) Analogue-to-digital converter
For convenience and rapidity of subsequent data processing, instantaneous values of the amplified pyrometer signal A0 are sampled by the
ADC 3 at a high frequency and converted to
multi-bit digital words Rio1, Ro2 R,,... etc. The frequency of sampling must be sufficiently high to ensure that insofar as the engine's fuel control system is concerned, the data processing is
performed effectively in real-time, so that there is very rapid response of the control system to significant changes in blade radiance
(temperature). The output from ADC 3 is processed in a two-stage operation by the following two functions.
(c) Filter function
Ways of performing this function are possible other than the one described here, but we prefer this one because of its simplicity and consistency of results.
The method of operation of this filter function 9 is described in our prior British Patent No.
1590835, to which the reader is referred, but basically filter function 9 comprises a temporary data store (i.e. a register), a comparator, an event recorder, and a gated output. Each new input data word Rio1, Ro2 Rio3... etc appearing on line 7 is compared with the data word already in the temporary data store. Each time the input data word is of less value than the stored data word, the input data word is allowed to enter the temporary data store, thus displacing the data word already there and becoming the new basis for comparison with later input data words.The number of comparisons is counted by the event recorder, and the output from the temporary data store is gated in such a way that if a predetermined number of consecutive input data words appear on line 7 without any of them being transferred to the temporary data store, the data word currently being held in the temporary data store will be taken to be valid data and will be outputted on line 11 as one of the data words AFI, AF2, ..... . etc. comprising the signal AF. Each RF data word will thus be the least of all the R values appearing on line 7 before the predetermined number is attained.Of course immediately after each RF output data word, the temporary store output gate is inhibited again, the register is re-set to its maximum value, the event recorder is also re-set to zero count, and the "filter" operation is repeated for the next set of A0 data words.
If the ADC 3 is triggered at a frequency f, and the "predetermined number" mentioned above is called n, it will be seen that the shortest possible period between successive RF data words will be n/f seconds, this being obtained only in the absence of interference in signal R,.
The predetermined number n must be set at a value which is large enough to avoid inadequate filtering of pyrometer radiance data, but small enough to enable the control signal A to give the fuel control system a sufficiently fast response to rapid changes in blade temperature. For instance, suppose that the integer number x of blades observed by the pyrometer is one and that frequency f is the same, or nearly the same, as the frequency with which the blades pass through the pyrometer's field of view; the lower limit for n is set by considering what magnitude for n gives an acceptably low probability that radiance due to combustion effects, such as tongues of flame or showers of radiant particles, will persist in the field of view for longer than the time is takes for n-1 blades to pass through the field of view.
In practice if x=1 we believe that n should be some fairly small fraction of the number of blades on the rotor, e.g. in the case of a rotor having about 144 blades n should be about 12.
Note that since signal RO (apart from interference) is a series of data words each of which is representative of the average radiance of the hottest parts of an integer number of blades, and that these data words may be subject to some variation in value between successive words due to the presence of blade-to-blade variations in average radiance, not only will filter function 9 filter out data words representing excessive interference in signal RO, but it will also select for onward transmission on line 11 those data words in signal RO which represent the least values of average blade radiance in each set of data words subjected to the filtering operation as described above.Hence, the filter function 9, as described above, acts both to remove interference from signal RO and to partially smooth it by rejecting at least some of the high average blade radiance values. Nevertheless, the filtered signal Ap may still exhibit variations in value which are too great to avoid excessive "hunting" of control signal A, especially if there is frequent interference in signal RO, and therefore the smoothing function 1 3 may be required.
(d) Smoothing function
Various alternative ways of performing this function exist. One simple way involves reading each successive data word AF1, RF2 At3 . . . etc on line 11 into a register capable of holding, say, five data words.Each time a new data word enters the register, the total contents (five data words) are summed and divided by five to give an output As (comprising successive data words Rust, Rs2, As3... etc) on line 1 5 which is a "moving average" of the input RF. If the capacity of the register is suitably chosen, together with suitable values of x, f and n, the output As will still effectively be in real-time as far as the reactiontime of the fuel control system to changes in engine condition is concerned, and each As data word can be taken to be representative of the instantaneous true average radiance of the hottest parts of all the blade aerofoils on the rotor (If the filter function 9 operates as detailed above, the values of R5 may in fact be a measure of radiances somewhat lower than the average radiance of all the blades on the rotor, since high radiance values from at least some of the hottest blades will have been eliminated from signal RF due to the "minimum picking" action of the filter function. However, this does not matter, since it can be allowed for in developmental calibration of the system, and hence it can still be said that signal Rs is representative of the true average
radiance of the hottest parts of all the blades.
The "cleaned up" blade radiance signal As may be regarded as the desired blade-temperaturedependent control signal to be fed to subsequent elements of the fuel control system. However, in order to be useable in controlling fuel flow, signal
R5 requires modification as follows.
(e) Linearising function
Linearising function 1 7 will not be required if subsequent elements of the fuel control system are able to utilise signals representative of blade radiance rather than blade temperature. However, for systems requiring temperature-derived signals, linearising function 1 7 is necessary to convert the blade radiance signal A5 to a blade temperature signal T.
Linearising function 17 is conveniently performed in a microprocessor programmed to fit successive data words Rust, Rs2, As3 . etc. to a predetermined radiance/temperature curve stored digitally in ROM, the output on line 19 being a succession of data words T1,T2, T3. . . etc which are representative of the (effective) real-time average temperature of all the blades.
(f) Production of control signal
In order to produce a control (feedback) signal for the rest of the fuel control system (here assumed to be of the digital type), it is necessary to compare signal T with a reference signal Tref in comparator function 21 and produce an output signal A comprising data words ht, A2, A3... etc, each of which represent a deviation from a null signal, the null signal being produced when no alteration of the fuel low due to turbine blade temperature is required.
The simplest case occurs when the apparatus herein described is only required to act as "top limiter" for turbine blade temperature. In such a case datum unit 23 generates a data word of constant value which is fed to the comparator function 21, this constant value representing the maximum allowable turbine blade average temperature. The comparator function performs the operation.
TrefT=A0 i.e. A is always either zero or negative and is used by the fuel control system to reduce fuel flow to the combustion chambers until an acceptable blade temperature is reached, provided this is compatible with safety or performance considerations.
If the apparatus herein described is required to provide a control signal which besides preventing overheating also maintains an optimum blade temperature under all conditions, thus permitting most efficient working of the engine without overheating, Tref must be a value which varies as selected engine parameters vary, such as throttle position, intake air temperature and pressure, rotor speed and acceleration, turbine gas temperature, and compressor or delivery pressure. In this more complex case, the output of datum unit 23 varies according to a predetermined ideal schedule of the engine parameters correlated with corresponding ideal blade temperatures. It is convenient if the unit comprises a microprocessor programmed with the schedule and receiving the engine parameter inputs in digital form.The output Tref then consists of values previously determined during tests to produce the best compromise between fuel economy and blade life usage at the various engine conditions, and the comparator function performs the operation TrefT=A where A may be zero, positive or negative and is used by the control system as a trimming signal in conjunction with other signals representing variation of other engine parameters.
Although the comparison function has been described in terms of comparison of temperature signals, it should be noted that in the absence of a requirement for the linearising function, it would be equally possible to compare the radiance signal As with a reference radiance signal generated by a suitably modified datum unit 23, and produce a control signal A which depended directly on blade radiance data rather than blade temperature data derived from blade radiance data.
In the above paragraphs, reference was made to the convenience of carrying out the linearising and scheduling functions in a microprocessor. It will be apparent that the filtering, smoothing and comparison functions could also be incorporated in a suitably programmed microprocessor.
Note that although the above description has been concerned with use of the invention to produce a control signal for a fuel control system, the signal A0 (in digital or analogue form) could be passed to known types of "peak-picking" circuitry synchronised with the frequency of passage of the blades through the field of view of the pyrometer in order to detect and positionally identify blades which are running at hotter temperatures than the others and which will thus have reduced operational life. Further, the signal on line 11 or line 1 5 could be utilised as an input to a device recording elapsed fatigue life for the typical blade on the rotor.
Claims (10)
1. Apparatus for generating a monitor signal for use in the operation of a gas turbine engine,
said monitor signal being dependent upon the temperatures of a stage of turbine rotor blades in the gas turbine engine, said apparatus including: optical radiation pyrometer means which in operation produces a radiance signal comprising a first component representative of the real-time average radiance of the hottest parts of an integer
number of turbine rotor blades, and a second
component due to transient interference from
non-blade sources of radiation, said integer
number being a fraction of the total number of
blades on the rotor; and signal processing means
adapted to derive said monitor signal from said
radiance signal.
2. Apparatus according to claim 1 in which the
signal processing means includes signal filtering
means adapted to filter out the second
component of the radiance signal.
3. Apparatus according to claim 2 in which the
signal processing means further includes signal smoothing means adapted to reduce the amplitude of fluctuations in the strength of the first component of the radiance signal.
4. Apparatus according to claim 2 in which the signal processing means further include signal generating means for generating a reference signal representing at least one predetermined blade radiance value and signal comparator means for comparing the reference signal with the filtered radiance signal and producing a further radiance signal dependence upon the difference between the values of the reference signal and the filtered radiance signal said further radiance signal being suitable as a control signal for a fuel control system of the gas turbine engine.
5. Apparatus according to claim 3 in which the signal processing means further includes signal generating means for generating a reference signal representing at least one predeteremined blade radiance value and signal comparator means for comparing the reference signal with the smoothed radiance signal and producing a further radiance signal in dependence upon the difference between the values of the reference signal and the smoothed radiance signal, said further radiance signal being suitable as a control signal for a fuel control system of the gas turbine engine.
6. Apparatus according to claim 2 in which the signal processing means further includes means for converting the filtered radiance signal to a first temperature signal, signal generating means for generating a reference signal representing at least one predetermined blade temperature value and signal comparator means for comparing the reference signal with the first temperature signal and producing a second temperature signal in dependence upon the difference between the values of the reference signal and the first temperature signal, said second temperature signal being suitable as a control signal for a fuel control system of the gas turbine engine.
7. Apparatus according to claim 3 in which the signal processing means further includes means for converting the smoothed radiance signal to a first temperature signal, signal generation means for generating a reference signal representing at least one predetermined blade temperature value, and signal comparator means for comparing the reference signal with the first temperature signal and producing a second temperature signal in dependence upon the difference between the values of the reference signal and the first temperature signal, said second temperature signal being suitable as a control signal for a fuel control system of the gas turbine engine.
8. Apparatus according to any one of claims 2 to 7 in which the signal filtering means comprises signal processing means adapted to operate according to claim 2 of our prior British patent number 1 590835.
9. Apparatus according to any one of claims 1 to 8 in which the optical radiation pyrometer means comprises an optical radiation pyrometer according to the invention claimed in our copending British patent application number 8330307.
10. Apparatus for providing a gas turbine engine fuel control system with a signal which is dependent upon the real-time average temperature of the hottest parts of an integer number of turbine rotor blades in the engine, substantially as described in this specification with reference to and as illustrated by the accompanying drawing.
1 A fuel control system for a gas turbine engine, said system including apparatus according to any one of claims 1 to 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08333670A GB2133877B (en) | 1982-12-24 | 1983-12-16 | Generation of a signal dependent upon temperature of gas turbine rotor blades |
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8236763 | 1982-12-24 | ||
| GB8236764 | 1982-12-24 | ||
| GB08330307A GB2134251B (en) | 1982-12-24 | 1983-11-14 | Optical radiation pyrometer |
| GB08333670A GB2133877B (en) | 1982-12-24 | 1983-12-16 | Generation of a signal dependent upon temperature of gas turbine rotor blades |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB8333670D0 GB8333670D0 (en) | 1984-01-25 |
| GB2133877A true GB2133877A (en) | 1984-08-01 |
| GB2133877B GB2133877B (en) | 1986-12-03 |
Family
ID=27449423
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08333670A Expired GB2133877B (en) | 1982-12-24 | 1983-12-16 | Generation of a signal dependent upon temperature of gas turbine rotor blades |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2133877B (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2599839A1 (en) * | 1986-06-05 | 1987-12-11 | Smiths Industries Plc | PYROMETRIC DEVICE FOR INDICATING THE TEMPERATURE OF THE BLADES OF A GAS TURBINE |
| DE4004408A1 (en) * | 1990-02-13 | 1991-08-14 | Ultrakust Electronic Gmbh | IR temp. sensor for high temps. |
| US5080496A (en) * | 1990-06-25 | 1992-01-14 | General Electric Company | Method and apparatus for compensated temperature prediction |
| US5203632A (en) * | 1992-04-24 | 1993-04-20 | The United States Of America As Represented By The Secretary Of The Air Force | Gas turbine pyrometer filtering system |
| US5226731A (en) * | 1992-05-28 | 1993-07-13 | Electric Power Research Institute | Apparatus for measuring rotor exhaust gas bulk temperature in a combustion turbine and method therefor |
| WO1995026017A1 (en) * | 1994-03-24 | 1995-09-28 | Cerberus Ag | Signal evaluation circuit for a movement detector |
| GB2313187A (en) * | 1996-05-17 | 1997-11-19 | Rotadata Ltd | Surface temperature profile detection |
| EP1227222A2 (en) * | 2000-12-28 | 2002-07-31 | General Electric Company | Utilization of pyrometer data to detect oxidation |
| US6733173B1 (en) * | 1996-12-19 | 2004-05-11 | Diamond Power International, Inc. | Pyrometer for measuring the temperature of a gas component within a furnace |
| EP1418312A2 (en) * | 2002-11-06 | 2004-05-12 | General Electric Company | Turbine blade oxidation monitoring and life prediction using neural network based diagnostic techniques in conjunction with pyrometer signals |
| EP1860281A2 (en) * | 2006-05-25 | 2007-11-28 | General Electric Company | Method for controlling blade tip clearance in a gas turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB972394A (en) * | 1962-01-10 | 1964-10-14 | Rolls Royce | Gas turbine engine |
| GB1104322A (en) * | 1965-05-24 | 1968-02-21 | Rolls Royce | Gas turbine engine |
| GB1292796A (en) * | 1969-04-21 | 1972-10-11 | Gen Electric | Improvements in temperature measurements in gas turbine engines |
| GB1411285A (en) * | 1972-07-06 | 1975-10-22 | Rolls Royce | Radiation pyrometers |
| GB2045425A (en) * | 1979-07-09 | 1980-10-29 | Negretti & Zambra Aviat Ltd | Detection of spurious high temperature sources in the field of view of a pyrometer |
| GB1590835A (en) * | 1976-11-12 | 1981-06-10 | Rolls Royce | Data processing methods and systems |
| GB1595423A (en) * | 1977-05-13 | 1981-08-12 | Rolls Royce | Control systems for apparatus |
| GB2088047A (en) * | 1980-11-17 | 1982-06-03 | United Technologies Corp | Electronic peak averaging circuit for a pyrometer |
-
1983
- 1983-12-16 GB GB08333670A patent/GB2133877B/en not_active Expired
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB972394A (en) * | 1962-01-10 | 1964-10-14 | Rolls Royce | Gas turbine engine |
| GB1104322A (en) * | 1965-05-24 | 1968-02-21 | Rolls Royce | Gas turbine engine |
| GB1292796A (en) * | 1969-04-21 | 1972-10-11 | Gen Electric | Improvements in temperature measurements in gas turbine engines |
| GB1411285A (en) * | 1972-07-06 | 1975-10-22 | Rolls Royce | Radiation pyrometers |
| GB1590835A (en) * | 1976-11-12 | 1981-06-10 | Rolls Royce | Data processing methods and systems |
| GB1595423A (en) * | 1977-05-13 | 1981-08-12 | Rolls Royce | Control systems for apparatus |
| GB2045425A (en) * | 1979-07-09 | 1980-10-29 | Negretti & Zambra Aviat Ltd | Detection of spurious high temperature sources in the field of view of a pyrometer |
| GB2088047A (en) * | 1980-11-17 | 1982-06-03 | United Technologies Corp | Electronic peak averaging circuit for a pyrometer |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2599839A1 (en) * | 1986-06-05 | 1987-12-11 | Smiths Industries Plc | PYROMETRIC DEVICE FOR INDICATING THE TEMPERATURE OF THE BLADES OF A GAS TURBINE |
| DE4004408A1 (en) * | 1990-02-13 | 1991-08-14 | Ultrakust Electronic Gmbh | IR temp. sensor for high temps. |
| EP0442351A1 (en) * | 1990-02-13 | 1991-08-21 | ULTRAKUST electronic GmbH | Infrared temperature sensor |
| US5169234A (en) * | 1990-02-13 | 1992-12-08 | Ultrakust Electronic Gmbh | Infrared temperature sensor |
| US5080496A (en) * | 1990-06-25 | 1992-01-14 | General Electric Company | Method and apparatus for compensated temperature prediction |
| US5203632A (en) * | 1992-04-24 | 1993-04-20 | The United States Of America As Represented By The Secretary Of The Air Force | Gas turbine pyrometer filtering system |
| US5226731A (en) * | 1992-05-28 | 1993-07-13 | Electric Power Research Institute | Apparatus for measuring rotor exhaust gas bulk temperature in a combustion turbine and method therefor |
| WO1995026017A1 (en) * | 1994-03-24 | 1995-09-28 | Cerberus Ag | Signal evaluation circuit for a movement detector |
| GB2313187A (en) * | 1996-05-17 | 1997-11-19 | Rotadata Ltd | Surface temperature profile detection |
| GB2313187B (en) * | 1996-05-17 | 1999-10-06 | Rotadata Ltd | Surface temperature detection |
| US6733173B1 (en) * | 1996-12-19 | 2004-05-11 | Diamond Power International, Inc. | Pyrometer for measuring the temperature of a gas component within a furnace |
| EP1227222A2 (en) * | 2000-12-28 | 2002-07-31 | General Electric Company | Utilization of pyrometer data to detect oxidation |
| US6579005B2 (en) * | 2000-12-28 | 2003-06-17 | General Electric Company | Utilization of pyrometer data to detect oxidation |
| EP1227222A3 (en) * | 2000-12-28 | 2004-01-02 | General Electric Company | Utilization of pyrometer data to detect oxidation |
| EP1418312A2 (en) * | 2002-11-06 | 2004-05-12 | General Electric Company | Turbine blade oxidation monitoring and life prediction using neural network based diagnostic techniques in conjunction with pyrometer signals |
| EP1418312A3 (en) * | 2002-11-06 | 2005-09-21 | General Electric Company | Turbine blade oxidation monitoring and life prediction using neural network based diagnostic techniques in conjunction with pyrometer signals |
| EP1860281A2 (en) * | 2006-05-25 | 2007-11-28 | General Electric Company | Method for controlling blade tip clearance in a gas turbine |
| EP1860281A3 (en) * | 2006-05-25 | 2012-08-01 | General Electric Company | Method for controlling blade tip clearance in a gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2133877B (en) | 1986-12-03 |
| GB8333670D0 (en) | 1984-01-25 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |