CN106523163B - Aero gas turbine engine surge controlling method and electronic controller - Google Patents
Aero gas turbine engine surge controlling method and electronic controller Download PDFInfo
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- CN106523163B CN106523163B CN201610992726.7A CN201610992726A CN106523163B CN 106523163 B CN106523163 B CN 106523163B CN 201610992726 A CN201610992726 A CN 201610992726A CN 106523163 B CN106523163 B CN 106523163B
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- turbine engine
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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 kind of aero gas turbine engine surge controlling method and electronic controller, by obtaining combustion chamber inlet pressure and high pressure rotor rotation speed change amount；According to the combustion chamber inlet pressure of acquisition, high pressure rotor rotation speed change amount and default surge detection strategy, the surge condition of aero gas turbine engine is judged；According to the surge condition for the aero gas turbine engine judged, surge control is carried out to aero gas turbine engine.Aero gas turbine engine surge controlling method and electronic controller provided by the invention, pass through the combustion chamber inlet pressure of acquisition, high pressure rotor rotation speed change amount and default surge detection strategy, judge the surge condition of aero gas turbine engine, and according to the surge condition for the aero gas turbine engine judged, surge control is carried out to aero gas turbine engine, surge detection precision is high, and the asthma effect that disappears is good, can effectively avoid aviation accident.
Description
Technical field
The present invention relates to aero gas turbine engine control field, especially, is related to a kind of aviation gas turbine and starts
Machine surge controlling method and electronic controller.
Background technology
Aero gas turbine engine not always works in actual motion under design point.Work as service condition
When changing, its compressor operating point meeting off-design point, flow instabilities can be produced under certain condition.Compressor surge
A kind of typical unstable period of engine, it is characterized in that air-flow occur along compressor axial direction low frequency, high amplitude
Air-flow oscillatory occurences, the pulsation of blower outlet stagnation pressure is very big, and significantly pulsing also occur in flow and speed, so as to cause to navigate
Air gas turbogenerator is flame-out and intense mechanical is vibrated, and the serious of aero gas turbine engine is caused in very short time
Damage.Therefore when there is engine surge, surge area should be immediately exited from, avoids accident.But the shortcomings that prior art
Be electronic controller do not possess detection engine whether the ability of surge, surge occur after, electronic controller can not be taken in time
Effective control method makes engine disappear asthma.
Therefore, the surge of aero gas turbine engine how is detected and eliminated, is technical school's problem urgently to be resolved hurrily.
The content of the invention
The invention provides a kind of aero gas turbine engine surge controlling method and electronic controller, to solve aviation
The surge detection of gas-turbine unit and the technical problem eliminated.
The technical solution adopted by the present invention is as follows：
According to an aspect of the present invention, there is provided a kind of aero gas turbine engine surge controlling method, including step：
Obtain combustion chamber inlet pressure and high pressure rotor rotation speed change amount；
According to the combustion chamber inlet pressure of acquisition, high pressure rotor rotation speed change amount and default surge detection strategy, sentence
The surge condition of disconnected aero gas turbine engine；
According to the surge condition for the aero gas turbine engine judged, surge is carried out to aero gas turbine engine
Control.
Further, examined according to the combustion chamber inlet pressure of acquisition, high pressure rotor rotation speed change amount and default surge
Strategy is surveyed, is included the step of the surge condition for judging aero gas turbine engine：
If the pulsation that the pulsating quantity ratio of the combustion chamber inlet pressure obtained is more than or equal at the surge critical point of setting
Measure ratio and high pressure rotor rotation speed change amount exceedes the rotating speed threshold values of setting, then assert that aero gas turbine engine is breathed heavily
Shake；Wherein, the ratio of pulsating quantity and average magnitude corresponding to the pulsating quantity ratio as surge critical point at surge critical point set；
Interpolation table of the rotating speed threshold values set as both local atmospheric pressure and normal atmospheric pressure ratio；And
The pulsating quantity ratio of combustion chamber inlet pressure is：
Wherein, A be combustion chamber inlet pressure pulsating quantity ratio, U1For the average magnitude of combustion chamber inlet pressure signal, U2For
The pulsating quantity of combustion chamber inlet pressure signal.
Further, the surge condition according to the aero gas turbine engine judged, starts to aviation gas turbine
The step of machine progress surge control, includes：
If detecting, surge occurs for aero gas turbine engine, passes through the compressor to aero gas turbine engine
Deflate, fuel flow and igniter fire control effectively up to surge eliminates.
Further, by being control effectively to the compressor bleed air of aero gas turbine engine the step of, includes：
The aviation in different motion state is fired by the air bleed valve aperture of default low-pressure compressor air bleed valve
The surge of gas eddy turbine is controlled；
The high-pressure compressor air bleed valve of aero gas turbine engine is carried out being turned on and off control to eliminate surge.
Further, by being control effectively to the fuel flow of aero gas turbine engine the step of, includes：
The aviation gas turbine in different motion state is sent out by the speed of service and default step-size factor of fuel oil
Motivation carries out surge control.
According to another aspect of the present invention, a kind of electronic controller for aero gas turbine engine is additionally provided,
Including：
Acquisition module, for obtaining combustion chamber inlet pressure and high pressure rotor rotation speed change amount；
Judge module, for the combustion chamber inlet pressure according to acquisition, high pressure rotor rotation speed change amount and default asthma
Shake inspection policies, judges the surge condition of aero gas turbine engine；
Surge control module, for the surge condition according to the aero gas turbine engine judged, to aircraft gas
Turbogenerator carries out surge control.
Further, judge module includes assert unit,
Unit is assert, if the surge that the pulsating quantity ratio of the combustion chamber inlet pressure for obtaining is more than or equal to setting is faced
Pulsating quantity ratio and high pressure rotor rotation speed change amount at boundary's point exceed the rotating speed threshold values of setting, then assert aviation gas turbine
Surge occurs for engine；Wherein, pulsating quantity corresponding to the pulsating quantity ratio as surge critical point at surge critical point set with
The ratio of average magnitude；Interpolation table of the rotating speed threshold values set as both local atmospheric pressure and normal atmospheric pressure ratio；And
The pulsating quantity ratio of combustion chamber inlet pressure is：
Wherein, A be combustion chamber inlet pressure pulsating quantity ratio, U1For the average magnitude of combustion chamber inlet pressure signal, U2For
The pulsating quantity of combustion chamber inlet pressure signal.
Surge control module includes surge and eliminates unit,
Surge eliminates unit, if for detecting that surge occurs for aero gas turbine engine, by aircraft gas
Compressor bleed air, fuel flow and the igniter fire of turbogenerator control effectively until surge eliminates.
Further, surge eliminates unit and put including low-pressure compressor air bleed valve control subelement and high-pressure compressor
Gas valve controls subelement,
Low-pressure compressor air bleed valve controls subelement, for being lived by the deflation of default low-pressure compressor air bleed valve
Surge of the door aperture to the aero gas turbine engine in different motion state is controlled；
High-pressure compressor air bleed valve controls subelement, for the high-pressure compressor deflation to aero gas turbine engine
Valve carries out being turned on and off control to eliminate surge.
Further, surge, which eliminates unit, also includes fuel flow control subelement,
Fuel flow controls subelement, for the speed of service by fuel oil and default step-size factor in different fortune
The aero gas turbine engine of dynamic state carries out surge control.
The invention has the advantages that：
Aero gas turbine engine surge controlling method and electronic controller provided by the invention, pass through the burning of acquisition
Room inlet pressure, high pressure rotor rotation speed change amount and default surge detection strategy, judge aero gas turbine engine
Surge condition, and according to the surge condition for the aero gas turbine engine judged, aero gas turbine engine is carried out
Surge controls.Aero gas turbine engine surge controlling method and electronic controller provided by the invention, surge detection precision
Height, the asthma effect that disappears is good, can effectively avoid aviation accident.
In addition to objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to figure, the present invention is further detailed explanation.
Brief description of the drawings
The accompanying drawing for forming the part of the application is used for providing a further understanding of the present invention, schematic reality of the invention
Apply example and its illustrate to be used to explain the present invention, do not form inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the schematic flow sheet of aero gas turbine engine surge controlling method first embodiment of the present invention；
Fig. 2 is the schematic flow sheet of aero gas turbine engine surge controlling method second embodiment of the present invention；
Fig. 3 is the schematic flow sheet of aero gas turbine engine surge controlling method 3rd embodiment of the present invention；
Fig. 4 is the schematic flow sheet of aero gas turbine engine surge controlling method fourth embodiment of the present invention；
Fig. 5 is the schematic flow sheet of the embodiment of aero gas turbine engine surge controlling method the 5th of the present invention；
Fig. 6 is the schematic flow sheet of aero gas turbine engine surge controlling method sixth embodiment of the present invention；
Fig. 7 is the structured flowchart for the electronic controller first embodiment that the present invention is used for aero gas turbine engine；
Fig. 8 is the high-level schematic functional block diagram of the preferred embodiment of judge module one in Fig. 7；
Fig. 9 is the high-level schematic functional block diagram of the preferred embodiment of surge control module one in Fig. 7；
Figure 10 is the high-level schematic functional block diagram that surge eliminates unit first embodiment in Fig. 9；
Figure 11 is the high-level schematic functional block diagram that surge eliminates unit second embodiment in Fig. 9；
Figure 12 is the high-level schematic functional block diagram that surge eliminates unit 3rd embodiment in Fig. 9.
Accompanying drawing marks explanation：
10th, acquisition module；20th, judge module；30th, surge control module；21st, unit is assert；31st, surge eliminates unit；
311st, low-pressure compressor air bleed valve control subelement；312nd, high-pressure compressor air bleed valve control subelement；313rd, fuel oil stream
Amount control subelement；314th, igniter fire control subelement.
Embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase
Mutually combination.Describe the present invention in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Reference picture 1, the preferred embodiments of the present invention provide a kind of aero gas turbine engine surge controlling method, bag
Include step：
Step S100, combustion chamber inlet pressure and high pressure rotor rotation speed change amount are obtained.
The combustion chamber inlet pressure (P3) and velocity sensor that electronic controller collection pressure sensor is sent pass
The high pressure rotor rotating speed brought, turned with obtaining the combustion chamber inlet pressure (P3) of aero gas turbine engine and high pressure rotor
Fast variable quantity (NHDot).
Step S200, examined according to the combustion chamber inlet pressure of acquisition, high pressure rotor rotation speed change amount and default surge
Strategy is surveyed, judges the surge condition of aero gas turbine engine.
Electronic controller according to the combustion chamber inlet pressure (P3) of acquisition, high pressure rotor rotation speed change amount (NHDot) and
Default surge detection strategy, judge the surge condition of aero gas turbine engine, wherein, it is set with surge detection strategy
Two conditions, think that surge occurs for aero gas turbine engine if following two conditions are provided simultaneously with：
a)A≥A0；Wherein,A0 is the ratio of pulsating quantity and average magnitude corresponding to surge critical point, and A0 takes
15.625% (being set with specific reference to the type of aero gas turbine engine), the average magnitudes of P3 signals are U1, pulsating quantity
For U2.
B) high pressure rotor rotation speed change amount (NHDot) exceedes the rotary speed threshold value of setting, wherein, as shown in table 1, rotary speed threshold value
It is the interpolation table on P1/P0, P1 is local atmospheric pressure, and P0 is normal atmospheric pressure.
| P1/P0 | NHDot (unit, 1/s) |
| 0.3 | 2.7% |
| 0.5 | 4.5% |
| 0.6 | 5.4% |
| 1 | 9% |
Table 1
Step S300, the surge condition according to the aero gas turbine engine judged, starts to aviation gas turbine
Machine carries out surge control.
Surge condition of the electronic controller according to the aero gas turbine engine judged, from compressor bleed air, fuel oil
Efficiently controlled in terms of flow and igniting, disappear asthma in time, can avoid the generation of aviation accident.
The aero gas turbine engine surge controlling method that the present embodiment provides, passes through the combustion chamber inlet-pressure of acquisition
Power, high pressure rotor rotation speed change amount and default surge detection strategy, judge the surge condition of aero gas turbine engine,
And according to the surge condition of aero gas turbine engine judged, surge control is carried out to aero gas turbine engine,
Surge detection precision is high, and the asthma effect that disappears is good, can effectively avoid aviation accident.
As shown in Fig. 2 the flow that Fig. 2 is aero gas turbine engine surge controlling method second embodiment of the present invention is shown
It is intended to, on the basis of first embodiment, the aero gas turbine engine surge controlling method of second embodiment offer, step
S200 includes：
Step S200A, if it is critical to be more than or equal to the surge set for the pulsating quantity ratio of the combustion chamber inlet pressure obtained
Pulsating quantity ratio and high pressure rotor rotation speed change amount at point exceed the rotating speed threshold values of setting, then assert aviation gas turbine hair
Surge occurs for motivation；Wherein, pulsating quantity corresponding to the pulsating quantity ratio as surge critical point at surge critical point set is with putting down
The ratio measured；Interpolation table of the rotating speed threshold values set as both local atmospheric pressure and normal atmospheric pressure ratio；And
The pulsating quantity ratio of combustion chamber inlet pressure is：
Wherein, A be combustion chamber inlet pressure pulsating quantity ratio, U1For the average magnitude of combustion chamber inlet pressure signal, U2For
The pulsating quantity of combustion chamber inlet pressure signal.
The present embodiment provide aero gas turbine engine surge controlling method, by default surge detection strategy come
The surge of aero gas turbine engine is detected, surge detection precision is high, and the asthma effect that disappears is good, effectively aviation accident can be avoided to send out
It is raw.
As shown in figure 3, the flow that Fig. 3 is aero gas turbine engine surge controlling method 3rd embodiment of the present invention is shown
It is intended to, on the basis of first embodiment, the aero gas turbine engine surge controlling method of 3rd embodiment offer, step
S300 includes：
If step S300A, detecting, surge occurs for aero gas turbine engine, by starting to aviation gas turbine
Compressor bleed air, fuel flow and the igniter fire of machine control effectively until surge eliminates.
If electronic controller detects that surge occurs for aero gas turbine engine, by starting to aviation gas turbine
Compressor bleed air, fuel flow and the igniter fire of machine control effectively until surge eliminates, such as controls low pressure pressure
The air bleed valve discharge quantity of mechanism of qi, the size of fuel flow and igniter fire time eliminate surge.
The aero gas turbine engine surge controlling method that the present embodiment provides, by aero gas turbine engine
Compressor bleed air, fuel flow and igniter fire control effectively until surge eliminate, disappear asthma effect it is good, can be effective
Avoid aviation accident.
As shown in figure 4, the flow that Fig. 4 is aero gas turbine engine surge controlling method fourth embodiment of the present invention is shown
It is intended to, on the basis of 3rd embodiment, the aero gas turbine engine surge controlling method of fourth embodiment offer, step
S300 includes：
Step S310, by the air bleed valve aperture of default low-pressure compressor air bleed valve in different motion state
The surge of aero gas turbine engine be controlled.
As shown in table 2, electronic controller by the air bleed valve aperture of default low-pressure compressor air bleed valve in
The surge of the aero gas turbine engine of different motion state is controlled, wherein, the aircraft gas whirlpool of different motion state
The surge when surge of turbine includes accelerating, surge and surge during stable state when slowing down.
Table 2
Step S320, the high-pressure compressor air bleed valve of aero gas turbine engine be turned on and off control with
Eliminate surge.
Electronic controller carries out being turned on and off controlling to the high-pressure compressor air bleed valve of aero gas turbine engine
To eliminate surge, disappear and be all turned on high-pressure compressor air bleed valve when breathing heavily；And high-pressure compressor deflation is then closed in remaining time
Valve.
The aero gas turbine engine surge controlling method that the present embodiment provides, is deflated by default low-pressure compressor
The air bleed valve aperture and high-pressure compressor air bleed valve of valve carry out being turned on and off control to eliminate surge, and disappear asthma effect
It is good, it can effectively avoid aviation accident.
As shown in figure 5, the flow that Fig. 5 is the embodiment of aero gas turbine engine surge controlling method the 5th of the present invention is shown
It is intended to, on the basis of fourth embodiment, the aero gas turbine engine surge controlling method of the 5th embodiment offer, step
S300 includes：
Step S330, the aviation in different motion state is fired by the speed of service and default step-size factor of fuel oil
Gas eddy turbine carries out surge control.
The flow control of electronic controller includes：
Fuel flow is controlled when a, to stable state：Disappear asthma when, slow down fuel oil growth rate, and step-size factor is set to
0.15, otherwise it is set to 0.75.
Fuel flow is controlled when b, to accelerating：After acceleration and deceleration voting, by oil-gas ratio when being directly disposed as surge
(wf/P3) fuel feeding is calculated.First, benchmark is gone out according to high pressure rotor corrected spool speed (NHC) and inlet pressure ratio (P1/P0) interpolation
Oil-gas ratio；Then combustion chamber inlet pressure (P3) is multiplied by, obtains oil-gas ratio restraining line fuel flow.
Fuel flow is controlled when c, to slowing down：It is quick to reduce fuel oil, and it is 0.75 to set step-size factor.
The aero gas turbine engine surge controlling method that the present embodiment provides, passes through the flow control to electronic controller
Make to eliminate surge, the asthma effect that disappears is good, can effectively avoid aviation accident.
As shown in fig. 6, the flow that Fig. 6 is aero gas turbine engine surge controlling method sixth embodiment of the present invention is shown
It is intended to, on the basis of the 5th embodiment, the aero gas turbine engine surge controlling method of sixth embodiment offer, step
S300 includes：
Step S340, by being controlled the duration of ignition of igniter to eliminate surge.
It is 5S that electronic controller when breathing heavily that disappears, which controls the duration of ignition of two igniters,.
The aero gas turbine engine surge controlling method that the present embodiment provides, by the duration of ignition to igniter
It is controlled to eliminate surge, the asthma effect that disappears is good, can effectively avoid aviation accident.
As shown in fig. 7, the present invention also provides a kind of electronic controller for aero gas turbine engine, including obtain
Module 10, for obtaining combustion chamber inlet pressure and high pressure rotor rotation speed change amount；Judge module 20, for the combustion according to acquisition
Room inlet pressure, high pressure rotor rotation speed change amount and default surge detection strategy are burnt, judges aero gas turbine engine
Surge condition；Surge control module 30, for the surge condition according to the aero gas turbine engine judged, to aviation
Gas-turbine unit carries out surge control.
The acquisition module 10 of electronic controller gather the combustion chamber inlet pressure (P3) that pressure sensor sends and
The high pressure rotor rotating speed that velocity sensor is sent, to obtain the combustion chamber inlet pressure (P3) of aero gas turbine engine
With high pressure rotor rotation speed change amount (NHDot).
Combustion chamber inlet pressure (P3) of the judge module 20 of electronic controller according to acquisition, high pressure rotor rotation speed change amount
(NHDot) surge condition of aero gas turbine engine and default surge detection strategy, is judged, wherein, surge detection
Two conditions are set with strategy, think that surge occurs for aero gas turbine engine if following two conditions are provided simultaneously with：
a)A≥A0；Wherein,A0 is the ratio of pulsating quantity and average magnitude corresponding to surge critical point, and A0 takes
15.625% (being set with specific reference to the type of aero gas turbine engine), the average magnitudes of P3 signals are U1, pulsating quantity
For U2.
B) high pressure rotor rotation speed change amount (NHDot) exceedes the rotary speed threshold value of setting, wherein, as shown in table 1, rotary speed threshold value
It is the interpolation table on P1/P0, P1 is local atmospheric pressure, and P0 is normal atmospheric pressure.
Surge condition of the surge control module 30 of electronic controller according to the aero gas turbine engine judged, from
Efficiently controlled in terms of compressor bleed air, fuel flow and igniting, disappear asthma in time, can avoid the generation of aviation accident.
The electronic controller for aero gas turbine engine that the present embodiment provides, passes through the combustion chamber import of acquisition
Pressure, high pressure rotor rotation speed change amount and default surge detection strategy, judge the surge shape of aero gas turbine engine
Condition, and according to the surge condition for the aero gas turbine engine judged, surge control is carried out to aero gas turbine engine
System, surge detection precision is high, and the asthma effect that disappears is good, can effectively avoid aviation accident.
As shown in figure 8, Fig. 8 is the high-level schematic functional block diagram of the preferred embodiment of judge module one in Fig. 7, in the present embodiment
In, judge module 20 includes assert unit 21, if assert, unit 21 is used for the pulsating quantity ratio of the combustion chamber inlet pressure of acquisition
More than or equal to the rotating speed that the pulsating quantity ratio at the surge critical point of setting and high pressure rotor rotation speed change amount exceed setting
Threshold values, then assert that surge occurs for aero gas turbine engine；Wherein, the pulsating quantity ratio at surge critical point set is asthma
The ratio for pulsating quantity corresponding to critical point and the average magnitude of shaking；The rotating speed threshold values set is local atmospheric pressure and normal atmospheric pressure
The interpolation table of both ratios；And
The pulsating quantity ratio of combustion chamber inlet pressure is：
Wherein, A be combustion chamber inlet pressure pulsating quantity ratio, U1For the average magnitude of combustion chamber inlet pressure signal, U2For
The pulsating quantity of combustion chamber inlet pressure signal.
The electronic controller for aero gas turbine engine that the present embodiment provides, passes through default surge detection plan
Slightly detect the surge of aero gas turbine engine, surge detection precision is high, the asthma effect that disappears is good, can effectively avoid aviation accident
Occur.
As shown in figure 9, Fig. 9 is the high-level schematic functional block diagram of the preferred embodiment of judge module one in Fig. 7, in the present embodiment
In, surge control module 30 includes surge and eliminates unit 31, if surge eliminates unit 31 and is used to detect that aviation gas turbine is sent out
Surge occurs for motivation, then by entering to the compressor bleed air of aero gas turbine engine, fuel flow and igniter fire
Row effectively control is until surge eliminates.
If the surge of electronic controller eliminates unit 31 and detects that surge occurs for aero gas turbine engine, by right
Compressor bleed air, fuel flow and the igniter fire of aero gas turbine engine control effectively until surge disappears
Remove, such as the air bleed valve discharge quantity of control low-pressure compressor, the size of fuel flow and igniter fire time eliminate
Surge.
The electronic controller for aero gas turbine engine that the present embodiment provides, by sending out aviation gas turbine
Compressor bleed air, fuel flow and the igniter fire of motivation control effectively until surge eliminates, and the asthma effect that disappears is good, can
Effectively avoid aviation accident.
As shown in Figure 10, Figure 10 is the high-level schematic functional block diagram that surge eliminates unit first embodiment in Fig. 9, in this implementation
In example, surge, which eliminates unit 31, includes low-pressure compressor air bleed valve control subelement 311 and high-pressure compressor air bleed valve control
Subunit 312, low-pressure compressor air bleed valve control subelement 311 are used for by default low-pressure compressor air bleed valve
Surge of the air bleed valve aperture to the aero gas turbine engine in different motion state is controlled；High-pressure compressor is put
Gas valve control subelement 312 is used to be turned on and off the high-pressure compressor air bleed valve of aero gas turbine engine
Control to eliminate surge.
As shown in table 2, the low-pressure compressor air bleed valve control subelement 311 of electronic controller passes through default low pressure pressure
Surge of the air bleed valve aperture of mechanism of qi air bleed valve to the aero gas turbine engine in different motion state is controlled
System, wherein, surge and stable state when the surge of the aero gas turbine engine of different motion state includes surge during acceleration, slowed down
When surge.
High pressure of the high-pressure compressor air bleed valve control subelement 312 of electronic controller to aero gas turbine engine
Compressor bleed air valve carries out being turned on and off control to eliminate surge, disappears and is all turned on high-pressure compressor air bleed valve when breathing heavily；
And then close high-pressure compressor air bleed valve in remaining time.
The electronic controller for aero gas turbine engine that the present embodiment provides, passes through default low-pressure compressor
The air bleed valve aperture and high-pressure compressor air bleed valve of air bleed valve carry out being turned on and off control to eliminate surge, and disappear asthma
Effect is good, can effectively avoid aviation accident.
As shown in figure 11, Figure 11 is the high-level schematic functional block diagram that surge eliminates unit second embodiment in Fig. 9, in this implementation
In example, surge, which eliminates unit 31, includes fuel flow control subelement 313, and fuel flow control subelement 313 is used to pass through combustion
The speed of service of oil and default step-size factor carry out surge control to the aero gas turbine engine in different motion state
System.
The flow control of the fuel flow control subelement 313 of electronic controller includes：
Fuel flow is controlled when a, to stable state：Disappear asthma when, slow down fuel oil growth rate, and step-size factor is set to
0.15, otherwise it is set to 0.75.
Fuel flow is controlled when b, to accelerating：After acceleration and deceleration voting, by oil-gas ratio when being directly disposed as surge
(wf/P3) fuel feeding is calculated.First, benchmark is gone out according to high pressure rotor corrected spool speed (NHC) and inlet pressure ratio (P1/P0) interpolation
Oil-gas ratio；Then combustion chamber inlet pressure (P3) is multiplied by, obtains oil-gas ratio restraining line fuel flow.
Fuel flow is controlled when c, to slowing down：It is quick to reduce fuel oil, and it is 0.75 to set step-size factor.
The electronic controller for aero gas turbine engine that the present embodiment provides, passes through the stream to electronic controller
Amount is controlled to eliminate surge, and the asthma effect that disappears is good, can effectively avoid aviation accident.
As shown in figure 12, Figure 12 is the high-level schematic functional block diagram that surge eliminates unit 3rd embodiment in Fig. 9, in this implementation
In example, surge, which eliminates unit 31, includes igniter fire control subelement 314, and igniter fire control subelement 314 is used to lead to
Cross and the duration of ignition of igniter is controlled to eliminate surge.
Disappear asthma when electronic controller igniter fire control subelement 314 control two igniters the duration of ignition be
5S。
The electronic controller for aero gas turbine engine that the present embodiment provides, by the igniting to igniter
Time is controlled to eliminate surge, and the asthma effect that disappears is good, can effectively avoid aviation accident.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (8)
1. a kind of aero gas turbine engine surge controlling method, it is characterised in that including step：
Obtain combustion chamber inlet pressure and high pressure rotor rotation speed change amount；
According to the combustion chamber inlet pressure of acquisition, the high pressure rotor rotation speed change amount and default surge detection plan
Slightly, the surge condition of the aero gas turbine engine is judged；
According to the surge condition for the aero gas turbine engine judged, the aero gas turbine engine is carried out
Surge controls；
It is described according to the combustion chamber inlet pressure of acquisition, the high pressure rotor rotation speed change amount and default surge detection
Strategy, include the step of the surge condition for judging the aero gas turbine engine：
If the pulsation that the pulsating quantity ratio of the combustion chamber inlet pressure obtained is more than or equal at the surge critical point of setting
Measure ratio and the high pressure rotor rotation speed change amount exceedes the rotating speed threshold values of setting, then assert that the aviation gas turbine starts
Surge occurs for machine；Wherein, pulsating quantity corresponding to the pulsating quantity ratio as surge critical point at the surge critical point set with
The ratio of average magnitude；Interpolation table of the rotating speed threshold values set as both local atmospheric pressure and normal atmospheric pressure ratio；
And
The pulsating quantity ratio of the combustion chamber inlet pressure is：
<mrow>
<mi>A</mi>
<mo>=</mo>
<mfrac>
<msub>
<mi>U</mi>
<mn>2</mn>
</msub>
<mrow>
<mn>2</mn>
<mo>&times;</mo>
<msub>
<mi>U</mi>
<mn>1</mn>
</msub>
</mrow>
</mfrac>
</mrow>
Wherein, A be combustion chamber inlet pressure pulsating quantity ratio, U1For the average magnitude of combustion chamber inlet pressure signal, U2For burning
The pulsating quantity of room inlet pressure signal.
2. aero gas turbine engine surge controlling method according to claim 1, it is characterised in that
The surge condition for the aero gas turbine engine that the foundation is judged, to the aero gas turbine engine
The step of carrying out surge control includes：
If detecting, surge occurs for the aero gas turbine engine, passes through the pressure to the aero gas turbine engine
Mechanism of qi is deflated, fuel flow and igniter fire control effectively up to surge eliminates.
3. aero gas turbine engine surge controlling method according to claim 2, it is characterised in that
It is described by being control effectively to the compressor bleed air of the aero gas turbine engine the step of include：
The aviation in different motion state is fired by the air bleed valve aperture of default low-pressure compressor air bleed valve
The surge of gas eddy turbine is controlled；
The high-pressure compressor air bleed valve of the aero gas turbine engine is carried out being turned on and off control to eliminate surge.
4. aero gas turbine engine surge controlling method according to claim 2, it is characterised in that
It is described by being control effectively to the fuel flow of the aero gas turbine engine the step of include：
The aviation gas turbine in different motion state is sent out by the speed of service and default step-size factor of fuel oil
Motivation carries out surge control.
A kind of 5. electronic controller for aero gas turbine engine, it is characterised in that including：
Acquisition module (10), for obtaining combustion chamber inlet pressure and high pressure rotor rotation speed change amount；
Judge module (20), for the combustion chamber inlet pressure according to acquisition, the high pressure rotor rotation speed change amount and
Default surge detection strategy, judge the surge condition of the aero gas turbine engine；
Surge control module (30), for the surge condition according to the aero gas turbine engine judged, to described
Aero gas turbine engine carries out surge control；
The judge module (20) includes assert unit (21),
The identification unit (21), if the pulsating quantity ratio of the combustion chamber inlet pressure for obtaining is more than or equal to setting
Surge critical point at pulsating quantity ratio and the high pressure rotor rotation speed change amount exceed setting rotating speed threshold values, then assert
Surge occurs for the aero gas turbine engine；Wherein, the pulsating quantity ratio at the surge critical point set is surge
The ratio of pulsating quantity corresponding to critical point and average magnitude；The rotating speed threshold values set is local atmospheric pressure and standard atmospheric pressure
The interpolation table of both power ratio；And
The pulsating quantity ratio of the combustion chamber inlet pressure is：
<mrow>
<mi>A</mi>
<mo>=</mo>
<mfrac>
<msub>
<mi>U</mi>
<mn>2</mn>
</msub>
<mrow>
<mn>2</mn>
<mo>&times;</mo>
<msub>
<mi>U</mi>
<mn>1</mn>
</msub>
</mrow>
</mfrac>
</mrow>
Wherein, A be combustion chamber inlet pressure pulsating quantity ratio, U1For the average magnitude of combustion chamber inlet pressure signal, U2For burning
The pulsating quantity of room inlet pressure signal.
6. the electronic controller according to claim 5 for aero gas turbine engine, it is characterised in that
The surge control module (30) includes surge and eliminates unit (31),
The surge eliminates unit (31), if for detecting that surge occurs for the aero gas turbine engine, by right
Compressor bleed air, fuel flow and the igniter fire of the aero gas turbine engine control effectively until surge
Eliminate.
7. the electronic controller according to claim 6 for aero gas turbine engine, it is characterised in that
The surge, which eliminates unit (31), includes low-pressure compressor air bleed valve control subelement (311) and high-pressure compressor deflation
Valve control subelement (312),
The low-pressure compressor air bleed valve control subelement (311), for passing through default low-pressure compressor air bleed valve
Surge of the air bleed valve aperture to the aero gas turbine engine in different motion state is controlled；
The high-pressure compressor air bleed valve control subelement (312), for the high pressure to the aero gas turbine engine
Compressor bleed air valve carries out being turned on and off control to eliminate surge.
8. the electronic controller according to claim 6 for aero gas turbine engine, it is characterised in that
The surge, which eliminates unit (31), includes fuel flow control subelement (313),
Fuel flow control subelement (313), for the speed of service by fuel oil and default step-size factor in
The aero gas turbine engine of different motion state carries out surge control.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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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| CN110131193B (en) * | 2018-02-02 | 2020-09-08 | 中国航发商用航空发动机有限责任公司 | Method and system for monitoring surge fault of aircraft engine |
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| CN109184913B (en) * | 2018-10-08 | 2019-12-20 | 南京航空航天大学 | Stability estimation and prediction-based active compound control method for aerodynamic stability of aircraft engine |
| CN110657031B (en) * | 2019-09-30 | 2020-10-23 | 山东超越数控电子股份有限公司 | Method for identifying surge of aircraft engine |
| CN110735669B (en) * | 2019-10-08 | 2021-12-28 | 中国航发沈阳发动机研究所 | Method and device for judging rotating stall of aviation gas turbine engine |
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| CN112594062B (en) * | 2020-11-13 | 2022-05-17 | 南京航空航天大学 | Simulation method for surge detection and surge elimination control verification |
| CN113482960B (en) * | 2021-06-23 | 2022-08-30 | 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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| CN106523163A (en) | 2017-03-22 |
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