CN106523163A - Surge control method and electronic controller for aero-gas turbine engine - Google Patents
Surge control method and electronic controller for aero-gas turbine engine Download PDFInfo
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- CN106523163A CN106523163A CN201610992726.7A CN201610992726A CN106523163A CN 106523163 A CN106523163 A CN 106523163A CN 201610992726 A CN201610992726 A CN 201610992726A CN 106523163 A CN106523163 A CN 106523163A
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- 238000000034 method Methods 0.000 title claims abstract description 40
- 238000002485 combustion reaction Methods 0.000 claims abstract description 48
- 238000001514 detection method Methods 0.000 claims abstract description 26
- 239000000446 fuel Substances 0.000 claims description 38
- 230000008030 elimination Effects 0.000 claims description 31
- 238000003379 elimination reaction Methods 0.000 claims description 31
- 230000000740 bleeding effect Effects 0.000 claims description 14
- 239000000295 fuel oil Substances 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 14
- 238000010586 diagram Methods 0.000 description 15
- 230000001133 acceleration Effects 0.000 description 6
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
The invention discloses a surge control method and an electronic controller for an aero-gas turbine engine. The surge control method comprises the following steps: acquiring inlet pressure of a combustion chamber and rotational speed variation of a high-pressure rotor; judging surge conditions of the aero-gas turbine engine according to the acquired inlet pressure of the combustion chamber and rotational speed variation of the high-pressure rotor, as well as a preset surge detection strategy; and performing surge control on the aero-gas turbine engine according to the judged surge conditions of the aero-gas turbine engine. According to the surge control method and the electronic controller for the aero-gas turbine engine, the surge conditions of the aero-gas turbine engine are judged according to the acquired inlet pressure of the combustion chamber and rotational speed variation of the high-pressure rotor, as well as the preset surge detection strategy, and surge control is performed on the aero-gas turbine engine according to the judged surge conditions of the aero-gas turbine engine, so that the surge detection accuracy is high, the surge eliminating effect is good, and air accidents can be effectively avoided.
Description
Technical Field
The invention relates to the field of aviation gas turbine engine control, in particular to an aviation gas turbine engine surge control method and an electronic controller.
Background
In actual operation, an aircraft gas turbine engine does not always operate under design conditions. When the operation condition changes, the working condition point of the compressor deviates from the design point, and unstable flow can be generated under a certain condition. The compressor surge is a typical unstable working condition of an engine and is characterized in that the phenomenon of low-frequency and high-amplitude airflow oscillation of airflow along the axial direction of a compressor is caused, the total pressure pulsation of an outlet of the compressor is very large, and the flow and the speed also have large-amplitude pulsation, so that the flameout and the strong mechanical vibration of an aviation gas turbine engine can be caused, and the aviation gas turbine engine can be seriously damaged in a very short time. Therefore, when the engine surging occurs, the engine surging area is immediately exited to avoid accidents. However, the prior art has the disadvantages that the electronic controller does not have the capability of detecting whether the engine surges or not, and after the surge occurs, the electronic controller cannot adopt an effective control method to eliminate the surge of the engine in time.
Therefore, how to detect and eliminate the surge of the aircraft gas turbine engine is an urgent technical and corrective problem to be solved.
Disclosure of Invention
The invention provides a surge control method and an electronic controller of an aviation gas turbine engine, which aim to solve the technical problem of surge detection and elimination of the aviation gas turbine engine.
The technical scheme adopted by the invention is as follows:
according to one aspect of the invention, there is provided an aircraft gas turbine engine surge control method comprising the steps of:
acquiring inlet pressure of a combustion chamber and variable quantity of the rotating speed of a high-pressure rotor;
judging the surge condition of the aviation gas turbine engine according to the acquired inlet pressure of the combustion chamber, the high-pressure rotor rotating speed variation and a preset surge detection strategy;
and carrying out surge control on the aviation gas turbine engine according to the judged surge condition of the aviation gas turbine engine.
Further, according to the acquired inlet pressure of the combustion chamber, the rotating speed variation of the high-pressure rotor and a preset surge detection strategy, the step of judging the surge condition of the aviation gas turbine engine comprises the following steps:
if the obtained pulsating quantity ratio of the inlet pressure of the combustion chamber is larger than or equal to the set pulsating quantity ratio at the surge critical point and the rotating speed variation of the high-pressure rotor exceeds the set rotating speed threshold value, determining that the aviation gas turbine engine generates surge; the set pulsating quantity ratio at the surge critical point is the ratio of the pulsating quantity corresponding to the surge critical point to the average quantity; the set rotating speed threshold value is an interpolation table of the ratio of the local atmospheric pressure to the standard atmospheric pressure; and
the pulsating quantity ratio of the inlet pressure of the combustion chamber is as follows:
wherein A is the pulsating quantity ratio of the inlet pressure of the combustion chamber, U1Is the average magnitude, U, of the combustion chamber inlet pressure signal2Is the pulsating amount of the combustor inlet pressure signal.
Further, the step of performing surge control on the aircraft gas turbine engine according to the determined surge condition of the aircraft gas turbine engine includes:
and if the aviation gas turbine engine is detected to generate surge, effectively controlling the air discharge of a compressor, the fuel flow and the ignition of an igniter of the aviation gas turbine engine until the surge is eliminated.
Further, the step of actively controlling compressor bleed air of the aircraft gas turbine engine comprises:
controlling surging of the aviation gas turbine engine in different motion states through preset opening degrees of air bleeding valves of the low-pressure compressor;
and opening or closing a high-pressure compressor bleed valve of the aviation gas turbine engine to eliminate surge.
Further, the step of efficiently controlling fuel flow to the aircraft gas turbine engine comprises:
and carrying out surge control on the aviation gas turbine engines in different motion states through the operating speed of the fuel oil and a preset step length coefficient.
According to another aspect of the present invention, there is also provided an electronic controller for an aircraft gas turbine engine, comprising:
the acquisition module is used for acquiring inlet pressure of a combustion chamber and the variable quantity of the rotating speed of the high-pressure rotor;
the judgment module is used for judging the surge condition of the aviation gas turbine engine according to the acquired inlet pressure of the combustion chamber, the rotating speed variation of the high-pressure rotor and a preset surge detection strategy;
and the surge control module is used for carrying out surge control on the aviation gas turbine engine according to the judged surge condition of the aviation gas turbine engine.
Further, the judging module comprises a confirming unit,
the determining unit is used for determining that the aviation gas turbine engine generates surge if the obtained pulsating quantity ratio of the inlet pressure of the combustion chamber is larger than or equal to the set pulsating quantity ratio at the surge critical point and the rotating speed variation of the high-pressure rotor exceeds the set rotating speed threshold; the set pulsating quantity ratio at the surge critical point is the ratio of the pulsating quantity corresponding to the surge critical point to the average quantity; the set rotating speed threshold value is an interpolation table of the ratio of the local atmospheric pressure to the standard atmospheric pressure; and
the pulsating quantity ratio of the inlet pressure of the combustion chamber is as follows:
wherein A is the pulsating quantity ratio of the inlet pressure of the combustion chamber, U1Is the average magnitude, U, of the combustion chamber inlet pressure signal2Is the pulsating amount of the combustor inlet pressure signal.
The surge control module includes a surge elimination unit,
and the surge eliminating unit is used for effectively controlling the air compressor air bleed, the fuel oil flow and the igniter ignition of the aviation gas turbine engine until the surge is eliminated if the aviation gas turbine engine is detected to generate the surge.
Further, the surge eliminating unit comprises a low-pressure compressor bleed valve sub-control subunit and a high-pressure compressor bleed valve control subunit,
the low-pressure compressor bleed valve control subunit is used for controlling surging of the aviation gas turbine engines in different motion states through preset bleed valve opening degrees of the low-pressure compressor bleed valves;
and the high-pressure compressor bleed valve control subunit is used for controlling the opening or closing of the high-pressure compressor bleed valve of the aviation gas turbine engine to eliminate surge.
Further, the surge elimination unit further comprises a fuel flow control subunit,
and the fuel flow control subunit is used for carrying out surge control on the aviation gas turbine engines in different motion states through the operating speed of the fuel and a preset step length coefficient.
The invention has the following beneficial effects:
according to the aviation gas turbine engine surge control method and the electronic controller, the obtained inlet pressure of the combustion chamber, the high-pressure rotor rotating speed variable quantity and the preset surge detection strategy are used for judging the surge condition of the aviation gas turbine engine, and the aviation gas turbine engine is subjected to surge control according to the judged surge condition of the aviation gas turbine engine. The aviation gas turbine engine surge control method and the electronic controller provided by the invention have the advantages of high surge detection precision and good surge elimination effect, and can effectively avoid aviation accidents.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic flow diagram of a first embodiment of an aircraft gas turbine engine surge control method of the present invention;
FIG. 2 is a schematic flow diagram of a second embodiment of an aircraft gas turbine engine surge control method of the present invention;
FIG. 3 is a schematic flow chart of a third embodiment of an aircraft gas turbine engine surge control method of the present invention;
FIG. 4 is a schematic flow chart diagram of a fourth embodiment of an aircraft gas turbine engine surge control method of the present invention;
FIG. 5 is a schematic flow chart of a fifth embodiment of an aircraft gas turbine engine surge control method of the present invention;
FIG. 6 is a schematic flow chart diagram of a sixth embodiment of an aircraft gas turbine engine surge control method of the present invention;
FIG. 7 is a block diagram of a first embodiment of an electronic controller for an aircraft gas turbine engine according to the present invention;
FIG. 8 is a functional block diagram of a preferred embodiment of the determination module of FIG. 7;
FIG. 9 is a functional block diagram of a preferred embodiment of the surge control module of FIG. 7;
FIG. 10 is a functional block diagram of a first embodiment of the surge elimination unit of FIG. 9;
FIG. 11 is a functional block diagram of a second embodiment of the surge elimination unit of FIG. 9;
fig. 12 is a functional block diagram of a third embodiment of the surge elimination unit in fig. 9.
Reference is made to the accompanying drawings in which:
10. an acquisition module; 20. a judgment module; 30. a surge control module; 21. a determination unit; 31. a surge elimination unit; 311. a control subunit of a deflation valve of the low-pressure compressor; 312. a control subunit of a deflation valve of the high-pressure compressor; 313. a fuel flow control subunit; 314. and an igniter ignition control subunit.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to FIG. 1, a preferred embodiment of the present invention provides an aircraft gas turbine engine surge control method comprising the steps of:
and S100, acquiring the inlet pressure of the combustion chamber and the variable quantity of the rotating speed of the high-pressure rotor.
And the electronic controller collects the combustion chamber inlet pressure (P3) transmitted by the pressure sensor and the high-pressure rotor rotating speed transmitted by the speed sensor so as to obtain the combustion chamber inlet pressure (P3) and the high-pressure rotor rotating speed variation (NHdot) of the aviation gas turbine engine.
And S200, judging the surge condition of the aviation gas turbine engine according to the acquired inlet pressure of the combustion chamber, the rotating speed variation of the high-pressure rotor and a preset surge detection strategy.
The electronic controller judges the surge condition of the aircraft gas turbine engine according to the acquired inlet pressure (P3) of the combustion chamber, the high-pressure rotor rotating speed variation (NHdot) and a preset surge detection strategy, wherein two conditions are set in the surge detection strategy, and if the two conditions are simultaneously met, the aircraft gas turbine engine is considered to generate surge:
a) a is more than or equal to A0; wherein,a0 is the ratio of the pulsating quantity to the average quantity corresponding to the surge critical point, A0 is 15.625% (specifically set according to the type of the aviation gas turbine engine), the average quantity of the P3 signal is U1, and the pulsating quantity is U2.
b) The high pressure rotor speed variation (NHdot) exceeds the set speed threshold, where the speed threshold is an interpolation table about P1/P0, P1 is the local atmospheric pressure, and P0 is the standard atmospheric pressure, as shown in Table 1.
| P1/P0 | NHdot (Unit, 1/s) |
| 0.3 | 2.7％ |
| 0.5 | 4.5％ |
| 0.6 | 5.4％ |
| 1 | 9％ |
TABLE 1
And step S300, carrying out surge control on the aviation gas turbine engine according to the judged surge condition of the aviation gas turbine engine.
The electronic controller effectively controls the aspects of air discharge of the air compressor, fuel flow and ignition according to the judged surge condition of the aviation gas turbine engine, timely eliminates the surge and can avoid the occurrence of aviation accidents.
According to the aviation gas turbine engine surge control method provided by the embodiment, the surge condition of the aviation gas turbine engine is judged through the acquired inlet pressure of the combustion chamber, the high-pressure rotor rotating speed variation and the preset surge detection strategy, and the aviation gas turbine engine is subjected to surge control according to the judged surge condition of the aviation gas turbine engine, so that the aviation gas turbine engine surge control method is high in surge detection precision and good in surge elimination effect, and can effectively avoid aviation accidents.
As shown in fig. 2, fig. 2 is a schematic flow chart of a second embodiment of the aircraft gas turbine engine surge control method of the present invention, and on the basis of the first embodiment, the second embodiment provides an aircraft gas turbine engine surge control method, and step S200 includes:
step S200A, if the obtained pulsating quantity ratio of the inlet pressure of the combustion chamber is larger than or equal to the set pulsating quantity ratio of the surge critical point and the rotating speed variation of the high-pressure rotor exceeds the set rotating speed threshold value, determining that the aircraft gas turbine engine generates surge; the set pulsating quantity ratio at the surge critical point is the ratio of the pulsating quantity corresponding to the surge critical point to the average quantity; the set rotating speed threshold value is an interpolation table of the ratio of the local atmospheric pressure to the standard atmospheric pressure; and
the pulsating quantity ratio of the inlet pressure of the combustion chamber is as follows:
wherein A is the pulsating quantity ratio of the inlet pressure of the combustion chamber, U1Is the average magnitude, U, of the combustion chamber inlet pressure signal2Is the pulsating amount of the combustor inlet pressure signal.
According to the aviation gas turbine engine surge control method provided by the embodiment, the surge of the aviation gas turbine engine is detected through a preset surge detection strategy, the surge detection precision is high, the surge elimination effect is good, and the aviation accident can be effectively avoided.
As shown in fig. 3, fig. 3 is a schematic flow chart of a third embodiment of the aircraft gas turbine engine surge control method according to the present invention, and on the basis of the first embodiment, the third embodiment provides an aircraft gas turbine engine surge control method, and step S300 includes:
and step S300A, if the aviation gas turbine engine is detected to generate surge, effectively controlling the compressor bleed air, the fuel flow and the igniter ignition of the aviation gas turbine engine until the surge is eliminated.
And if the electronic controller detects that the aviation gas turbine engine surges, effectively controlling the gas discharge of a compressor, the fuel flow and the ignition of an igniter of the aviation gas turbine engine until the surge is eliminated, for example, controlling the gas discharge amount of a gas discharge valve of a low-pressure compressor, the fuel flow and the ignition time of the igniter to eliminate the surge.
According to the aviation gas turbine engine surge control method provided by the embodiment, the air discharge of the compressor, the fuel flow and the ignition of the igniter of the aviation gas turbine engine are effectively controlled until the surge is eliminated, the surge elimination effect is good, and the occurrence of aviation accidents can be effectively avoided.
As shown in fig. 4, fig. 4 is a schematic flow chart of a fourth embodiment of the aircraft gas turbine engine surge control method according to the present invention, and on the basis of the third embodiment, the fourth embodiment provides an aircraft gas turbine engine surge control method, and step S300 includes:
and S310, controlling surging of the aviation gas turbine engine in different motion states through preset opening degree of the air bleeding valve of the low-pressure compressor.
As shown in table 2, the electronic controller controls the surging of the aircraft gas turbine engine in different motion states through the preset opening degree of the bleed valve of the low-pressure compressor, wherein the surging of the aircraft gas turbine engine in different motion states includes surging at the time of acceleration, surging at the time of deceleration and surging at the time of steady state.
TABLE 2
And step S320, opening or closing a high-pressure compressor bleed valve of the aviation gas turbine engine to eliminate surge.
The electronic controller controls the opening or closing of a high-pressure compressor bleed valve of the aviation gas turbine engine to eliminate surge, and the high-pressure compressor bleed valve is completely opened during surge elimination; and the air bleeding valve of the high-pressure compressor is closed in the rest time.
According to the aviation gas turbine engine surge control method provided by the embodiment, the surge is eliminated by controlling the opening degree of the preset air bleeding valve of the low-pressure compressor air bleeding valve and the opening or closing of the high-pressure compressor air bleeding valve, the surge eliminating effect is good, and the occurrence of aviation accidents can be effectively avoided.
As shown in fig. 5, fig. 5 is a schematic flow chart of a fifth embodiment of the aircraft gas turbine engine surge control method according to the present invention, and on the basis of the fourth embodiment, the fifth embodiment provides the aircraft gas turbine engine surge control method, and step S300 includes:
and S330, performing surge control on the aviation gas turbine engines in different motion states through the operating speed of the fuel oil and a preset step length coefficient.
The flow control of the electronic controller comprises:
a. controlling the fuel flow in a steady state: when eliminating surge, the fuel increase speed is slowed down, and the step coefficient is set to 0.15, otherwise, the step coefficient is set to 0.75.
b. Controlling the fuel flow during acceleration: after the acceleration and deceleration voting, the oil supply is directly calculated according to the oil-gas ratio (wf/P3) when the surge is set. Firstly, interpolating a reference oil-gas ratio according to a high-pressure rotor converted rotating speed (NHC) and an inlet pressure ratio (P1/P0); the fuel-air ratio limit line fuel flow is then obtained by multiplying the combustion chamber inlet pressure (P3).
c. Controlling the fuel flow during deceleration: the fuel is reduced rapidly and the step factor is set to 0.75.
The aviation gas turbine engine surge control method provided by the embodiment eliminates surge through flow control of the electronic controller, has a good surge elimination effect, and can effectively avoid aviation accidents.
As shown in fig. 6, fig. 6 is a schematic flow chart of a sixth embodiment of the aircraft gas turbine engine surge control method according to the present invention, and on the basis of the fifth embodiment, the sixth embodiment provides the aircraft gas turbine engine surge control method, and step S300 includes:
step S340, controlling the ignition time of the igniter to eliminate surge.
When the surge is eliminated, the electronic controller controls the ignition time of the two igniters to be 5S.
The aviation gas turbine engine surge control method provided by the embodiment eliminates surge by controlling the ignition time of the igniter, has good surge elimination effect, and can effectively avoid aviation accidents.
As shown in FIG. 7, the present invention also provides an electronic controller for an aircraft gas turbine engine, comprising an acquisition module 10 for acquiring combustor inlet pressure and high pressure rotor speed variation; the judging module 20 is used for judging the surge condition of the aviation gas turbine engine according to the acquired inlet pressure of the combustion chamber, the rotating speed variation of the high-pressure rotor and a preset surge detection strategy; and the surge control module 30 is used for carrying out surge control on the aviation gas turbine engine according to the judged surge condition of the aviation gas turbine engine.
An acquisition module 10 of the electronic controller acquires the combustor inlet pressure (P3) transmitted by the pressure sensor and the high-pressure rotor speed transmitted by the speed sensor to acquire the combustor inlet pressure (P3) and the high-pressure rotor speed variation (NHDot) of the aircraft gas turbine engine.
The judgment module 20 of the electronic controller judges the surge condition of the aircraft gas turbine engine according to the acquired combustion chamber inlet pressure (P3), the high-pressure rotor rotation speed variation (NHdot) and a preset surge detection strategy, wherein two conditions are set in the surge detection strategy, and if the two conditions are met at the same time, the aircraft gas turbine engine is considered to surge:
a) a is more than or equal to A0; wherein,a0 is the ratio of the pulsating quantity to the average quantity corresponding to the surge critical point, A0 is 15.625% (specifically set according to the type of the aviation gas turbine engine), the average quantity of the P3 signal is U1, and the pulsating quantity is U2.
b) The high pressure rotor speed variation (NHdot) exceeds the set speed threshold, where the speed threshold is an interpolation table about P1/P0, P1 is the local atmospheric pressure, and P0 is the standard atmospheric pressure, as shown in Table 1.
The surge control module 30 of the electronic controller effectively controls the aspects of air discharge, fuel flow and ignition of the compressor according to the judged surge condition of the aviation gas turbine engine, so that the surge is eliminated in time, and the occurrence of aviation accidents can be avoided.
The electronic controller for the aviation gas turbine engine provided by the embodiment judges the surge condition of the aviation gas turbine engine through the acquired inlet pressure of the combustion chamber, the high-pressure rotor rotating speed variation and the preset surge detection strategy, and performs surge control on the aviation gas turbine engine according to the judged surge condition of the aviation gas turbine engine, so that the surge detection precision is high, the surge elimination effect is good, and the aviation accident can be effectively avoided.
As shown in fig. 8, fig. 8 is a functional module schematic diagram of a preferred embodiment of the determination module in fig. 7, in this embodiment, the determination module 20 includes a determination unit 21, and the determination unit 21 is configured to determine that the aircraft gas turbine engine generates surge if the obtained pulsating quantity ratio of the combustor inlet pressure is greater than or equal to the set pulsating quantity ratio at the surge critical point and the high-pressure rotor rotation speed variation exceeds the set rotation speed threshold; the set pulsating quantity ratio at the surge critical point is the ratio of the pulsating quantity corresponding to the surge critical point to the average quantity; the set rotating speed threshold value is an interpolation table of the ratio of the local atmospheric pressure to the standard atmospheric pressure; and
the pulsating quantity ratio of the inlet pressure of the combustion chamber is as follows:
wherein A is the pulsating quantity ratio of the inlet pressure of the combustion chamber, U1Is the average magnitude, U, of the combustion chamber inlet pressure signal2Is the pulsating amount of the combustor inlet pressure signal.
The electronic controller for the aviation gas turbine engine provided by the embodiment detects the surge of the aviation gas turbine engine through a preset surge detection strategy, has high surge detection precision and good surge elimination effect, and can effectively avoid the occurrence of aviation accidents.
As shown in fig. 9, fig. 9 is a functional block diagram of a preferred embodiment of the determination module in fig. 7, in this embodiment, the surge control module 30 includes a surge elimination unit 31, and the surge elimination unit 31 is configured to effectively control compressor bleed air, fuel flow and igniter ignition of the aircraft gas turbine engine until the surge is eliminated if the aircraft gas turbine engine detects the occurrence of the surge.
If the surge elimination unit 31 of the electronic controller detects that the aviation gas turbine engine generates surge, the gas discharge of the compressor, the fuel flow and the ignition of the igniter of the aviation gas turbine engine are effectively controlled until the surge is eliminated, for example, the gas discharge amount of the gas discharge valve of the low-pressure compressor, the size of the fuel flow and the ignition time of the igniter are controlled to eliminate the surge.
The electronic controller for the aviation gas turbine engine provided by the embodiment effectively controls the air discharge of the compressor, the fuel flow and the ignition of the igniter of the aviation gas turbine engine until the surge is eliminated, has a good surge eliminating effect, and can effectively avoid the occurrence of aviation accidents.
As shown in fig. 10, fig. 10 is a functional block schematic diagram of a first embodiment of the surge elimination unit in fig. 9, in this embodiment, the surge elimination unit 31 includes a low-pressure compressor bleed valve control subunit 311 and a high-pressure compressor bleed valve control subunit 312, and the low-pressure compressor bleed valve control subunit 311 is configured to control the surge of the aircraft gas turbine engine in different motion states through preset bleed valve opening degrees of the low-pressure compressor bleed valve; the high pressure compressor bleed valve control subunit 312 is used to control the opening or closing of a high pressure compressor bleed valve of an aircraft gas turbine engine to eliminate surge.
As shown in table 2, the low-pressure compressor bleed valve control subunit 311 of the electronic controller controls the surge of the aircraft gas turbine engine in different motion states according to the preset bleed valve opening degree of the low-pressure compressor bleed valve, where the surge of the aircraft gas turbine engine in different motion states includes the surge at the time of acceleration, the surge at the time of deceleration, and the surge at the time of steady state.
The high-pressure compressor bleed valve control subunit 312 of the electronic controller controls the opening or closing of the high-pressure compressor bleed valve of the aircraft gas turbine engine to eliminate surge, and the high-pressure compressor bleed valve is completely opened during the surge elimination; and the air bleeding valve of the high-pressure compressor is closed in the rest time.
The electronic controller for the aviation gas turbine engine provided by the embodiment eliminates surge through opening or closing control of the preset air bleeding valve of the low-pressure compressor air bleeding valve and the preset air bleeding valve of the high-pressure compressor air bleeding valve, has a good anti-surge effect, and can effectively avoid the occurrence of aviation accidents.
As shown in fig. 11, fig. 11 is a functional block diagram of a second embodiment of surge elimination unit in fig. 9, and in this embodiment, surge elimination unit 31 includes a fuel flow control subunit 313, and fuel flow control subunit 313 is used for performing surge control on the aircraft gas turbine engine in different motion states through the operating speed of fuel and a preset step factor.
The flow control of the fuel flow control subunit 313 of the electronic controller includes:
a. controlling the fuel flow in a steady state: when eliminating surge, the fuel increase speed is slowed down, and the step coefficient is set to 0.15, otherwise, the step coefficient is set to 0.75.
b. Controlling the fuel flow during acceleration: after the acceleration and deceleration voting, the oil supply is directly calculated according to the oil-gas ratio (wf/P3) when the surge is set. Firstly, interpolating a reference oil-gas ratio according to a high-pressure rotor converted rotating speed (NHC) and an inlet pressure ratio (P1/P0); the fuel-air ratio limit line fuel flow is then obtained by multiplying the combustion chamber inlet pressure (P3).
c. Controlling the fuel flow during deceleration: the fuel is reduced rapidly and the step factor is set to 0.75.
The electronic controller for the aviation gas turbine engine provided by the embodiment eliminates surge through flow control of the electronic controller, has a good surge elimination effect, and can effectively avoid aviation accidents.
As shown in fig. 12, fig. 12 is a functional block diagram of a third embodiment of the surge elimination unit in fig. 9, and in this embodiment, the surge elimination unit 31 includes an igniter ignition control subunit 314, and the igniter ignition control subunit 314 is configured to eliminate surge by controlling an ignition timing of an igniter.
The igniter ignition control subunit 314 of the electronic controller controls the ignition time of both the igniters to be 5S.
The electronic controller for the aviation gas turbine engine provided by the embodiment eliminates surge by controlling the ignition time of the igniter, has good surge elimination effect, and can effectively avoid the occurrence of aviation accidents.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An aircraft gas turbine engine surge control method, comprising the steps of:
acquiring inlet pressure of a combustion chamber and variable quantity of the rotating speed of a high-pressure rotor;
judging the surge condition of the aviation gas turbine engine according to the acquired inlet pressure of the combustion chamber, the rotating speed variation of the high-pressure rotor and a preset surge detection strategy;
and carrying out surge control on the aviation gas turbine engine according to the judged surge condition of the aviation gas turbine engine.
2. The aircraft gas turbine engine surge control method of claim 1,
the step of judging the surge condition of the aviation gas turbine engine according to the acquired inlet pressure of the combustion chamber, the high-pressure rotor rotating speed variation and a preset surge detection strategy comprises the following steps:
if the obtained pulsating quantity ratio of the inlet pressure of the combustion chamber is larger than or equal to the set pulsating quantity ratio at the surge critical point and the rotating speed variation of the high-pressure rotor exceeds the set rotating speed threshold value, determining that the aviation gas turbine engine generates surge; the set pulsating quantity ratio at the surge critical point is the ratio of the pulsating quantity corresponding to the surge critical point to the average quantity; the set rotating speed threshold value is an interpolation table of the ratio of the local atmospheric pressure to the standard atmospheric pressure; and
the pulsating quantity ratio of the inlet pressure of the combustion chamber is as follows:
wherein A is the pulsating quantity ratio of the inlet pressure of the combustion chamber, U1Is the average magnitude, U, of the combustion chamber inlet pressure signal2Is the pulsating amount of the combustor inlet pressure signal.
3. The aircraft gas turbine engine surge control method of claim 1,
the step of performing surge control on the aviation gas turbine engine according to the judged surge condition of the aviation gas turbine engine comprises the following steps of:
and if the aviation gas turbine engine is detected to generate surge, effectively controlling the air compressor deflation, the fuel flow and the igniter ignition of the aviation gas turbine engine until the surge is eliminated.
4. The aircraft gas turbine engine surge control method of claim 3,
the step of actively controlling compressor bleed air of the aircraft gas turbine engine comprises:
controlling surging of the aviation gas turbine engine in different motion states through preset opening degrees of air bleeding valves of the low-pressure compressor;
and controlling the opening or closing of a high-pressure compressor bleed valve of the aviation gas turbine engine to eliminate surge.
5. The aircraft gas turbine engine surge control method of claim 3,
the step of actively controlling the fuel flow of the aircraft gas turbine engine comprises:
and carrying out surge control on the aviation gas turbine engine in different motion states through the operating speed of the fuel oil and a preset step length coefficient.
6. An electronic controller for an aircraft gas turbine engine, comprising:
the acquisition module (10) is used for acquiring inlet pressure of a combustion chamber and the variable quantity of the rotating speed of the high-pressure rotor;
the judging module (20) is used for judging the surge condition of the aviation gas turbine engine according to the acquired inlet pressure of the combustion chamber, the rotating speed variation of the high-pressure rotor and a preset surge detection strategy;
and the surge control module (30) is used for carrying out surge control on the aviation gas turbine engine according to the judged surge condition of the aviation gas turbine engine.
7. The electronic controller for an aircraft gas turbine engine of claim 6,
the judging module (20) comprises a recognizing unit (21),
the determining unit (21) is used for determining that the aviation gas turbine engine generates surge if the obtained pulsating quantity ratio of the inlet pressure of the combustion chamber is larger than or equal to the set pulsating quantity ratio at the surge critical point and the rotating speed variation of the high-pressure rotor exceeds the set rotating speed threshold; the set pulsating quantity ratio at the surge critical point is the ratio of the pulsating quantity corresponding to the surge critical point to the average quantity; the set rotating speed threshold value is an interpolation table of the ratio of the local atmospheric pressure to the standard atmospheric pressure; and
the pulsating quantity ratio of the inlet pressure of the combustion chamber is as follows:
wherein A is the pulsating quantity ratio of the inlet pressure of the combustion chamber, U1Is the average magnitude, U, of the combustion chamber inlet pressure signal2Is the pulsating amount of the combustor inlet pressure signal.
8. The electronic controller for an aircraft gas turbine engine of claim 6,
the surge control module (30) comprises a surge elimination unit (31),
and the surge elimination unit (31) is used for effectively controlling the air compressor air bleed, the fuel flow and the igniter ignition of the aviation gas turbine engine until the surge is eliminated if the aviation gas turbine engine is detected to generate the surge.
9. The electronic controller for an aircraft gas turbine engine of claim 8,
the surge eliminating unit (31) comprises a low-pressure compressor bleed valve control subunit (311) and a high-pressure compressor bleed valve control subunit (312),
the low-pressure compressor bleed valve control subunit (311) is used for controlling surging of the aviation gas turbine engine in different motion states through preset bleed valve opening degrees of the low-pressure compressor bleed valve;
and the high-pressure compressor air bleeding valve control subunit (312) is used for controlling the opening or closing of the high-pressure compressor air bleeding valve of the aviation gas turbine engine so as to eliminate surge.
10. The electronic controller for an aircraft gas turbine engine of claim 8,
the surge elimination unit (31) comprises a fuel flow control subunit (313),
the fuel flow control subunit (313) is used for carrying out surge control on the aviation gas turbine engine in different motion states through the operating speed of fuel and a preset step length coefficient.
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| CN109184913A (en) * | 2018-10-08 | 2019-01-11 | 南京航空航天大学 | The aero-engine aerodynamic stability active composite control method with prediction is estimated based on stability |
| CN110131193A (en) * | 2018-02-02 | 2019-08-16 | 中国航发商用航空发动机有限责任公司 | Aero-engine surge fault monitoring method and system |
| CN110657991A (en) * | 2018-06-29 | 2020-01-07 | 中国航发商用航空发动机有限责任公司 | Surge monitoring method and surge monitoring system of aircraft engine |
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| CN113482960A (en) * | 2021-06-23 | 2021-10-08 | 中国航发沈阳发动机研究所 | Method for judging surge of aviation gas turbine engine |
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