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
- Publication number
- 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
- Authority
- CN
- China
- Prior art keywords
- surge
- gas turbine
- turbine engine
- aero gas
- aero
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
-
- 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
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 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 under design point in actual motion.Work as service condition
When changing, its compressor operating point meeting off-design point can produce flow instabilities under certain condition.Compressor surge
It is a kind of typical unstable period of engine, it is characterized in that low frequency, high amplitude that air-flow occurs along compressor axial direction
Air-flow oscillatory occurences, the pulsation of blower outlet stagnation pressure are very big, and significantly pulsing also occur in flow and speed, so as to cause boat
Air-fuel air turbine engine misses and intense mechanical vibration, 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, it is to avoid accident occurs.But the shortcoming of prior art
It is that electronic controller does not possess the detection engine whether ability of surge, after surge occurs, electronic controller can not be taken in time
Effectively control method makes engine disappear to breathe heavily.
Therefore, the surge of aero gas turbine engine how is detected and is 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 for eliminating.
The technical solution used in 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, high pressure rotor rotation speed change amount and default surge detection strategy that obtain, sentence
The surge condition of disconnected aero gas turbine engine；
According to the surge condition of the aero gas turbine engine judged, surge is carried out to aero gas turbine engine
Control.
Further, according to the combustion chamber inlet pressure, high pressure rotor rotation speed change amount and default surge inspection for obtaining
The step of surveying strategy, the surge condition for judging aero gas turbine engine includes：
If the pulsating quantity ratio of the combustion chamber inlet pressure for obtaining is more than or equal to the pulsation at the surge critical point of setting
Amount ratio and high pressure rotor rotation speed change amount exceed the rotating speed threshold values of setting, then assert that aero gas turbine engine is breathed heavily
Shake；Wherein, the pulsating quantity ratio at surge critical point for setting is the corresponding pulsating quantity of surge critical point and the ratio of average magnitude；
Interpolation table of the rotating speed threshold values for setting as both local atmospheric pressure and normal atmospheric pressure ratio；And
The pulsating quantity ratio of combustion chamber inlet pressure is：
Wherein, pulsating quantity ratios of the A for combustion chamber inlet pressure, U1For the average magnitude of combustion chamber inlet pressure signal, U2For
The pulsating quantity of combustion chamber inlet pressure signal.
Further, according to the surge condition of the aero gas turbine engine judged, aviation gas turbine is started
Machine carries out the step of surge is controlled to be included：
If detecting aero gas turbine engine there is surge, by the compressor to aero gas turbine engine
Deflate, fuel flow and igniter fire control effectively up to surge and eliminate.
Further, the step of being control effectively by the compressor bleed air to aero gas turbine engine is included：
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；
Carry out being turned on and off control to eliminate surge to the high-pressure compressor air bleed valve of aero gas turbine engine.
Further, the step of being control effectively by the fuel flow to aero gas turbine engine is included：
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 a further aspect in the 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 according to the combustion chamber inlet pressure, high pressure rotor rotation speed change amount for obtaining and default breathing heavily
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 identification unit,
Assert unit, if the pulsating quantity ratio of the combustion chamber inlet pressure for obtaining faces more than or equal to the surge of setting
Pulsating quantity ratio and high pressure rotor rotation speed change amount at boundary's point exceedes the rotating speed threshold values of setting, then assert aviation gas turbine
There is surge in engine；Wherein, the pulsating quantity ratio at surge critical point for setting as the corresponding pulsating quantity of surge critical point with
The ratio of average magnitude；Interpolation table of the rotating speed threshold values for setting as both local atmospheric pressure and normal atmospheric pressure ratio；And
The pulsating quantity ratio of combustion chamber inlet pressure is：
Wherein, pulsating quantity ratios of the A for combustion chamber inlet pressure, U1For the average magnitude of combustion chamber inlet pressure signal, U2For
The pulsating quantity of combustion chamber inlet pressure signal.
Surge control module includes that surge eliminates unit,
Surge eliminates unit, if there is surge for detecting aero gas turbine engine, by aircraft gas
The compressor bleed air of turbogenerator, fuel flow and igniter fire control effectively until surge is eliminated.
Further, surge eliminates unit includes that low-pressure compressor air bleed valve control subelement and high-pressure compressor are put
Gas valve controls subelement,
Low-pressure compressor air bleed valve controls subelement, lives for the deflation by 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, deflates for the high-pressure compressor to aero gas turbine engine
Valve carries out being turned on and off control to eliminate surge.
Further, surge eliminates unit also includes that fuel flow controls subelement,
Fuel flow controls subelement, for being transported to being in difference by the speed of service and default step-size factor of fuel oil
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 that the present invention is provided, by the burning for obtaining
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 of the aero gas turbine engine judged, aero gas turbine engine is carried out
Surge is controlled.Aero gas turbine engine surge controlling method and electronic controller that the present invention is provided, surge detection precision
Height, disappearing, it is good to breathe heavily effect, can be prevented effectively from aviation accident generation.
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.
Description of the drawings
The accompanying drawing for constituting the part of the application is used for providing a further understanding of the present invention, the schematic reality of the present invention
Apply example and its illustrate, for explaining the present invention, not constituting 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 5th embodiment of aero gas turbine engine surge controlling method 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 structured flowchart of the present invention for the electronic controller first embodiment of aero gas turbine engine；
Fig. 8 is the high-level schematic functional block diagram of one preferred embodiment of judge module in Fig. 7；
Fig. 9 is the high-level schematic functional block diagram of one preferred embodiment of surge control module in Fig. 7；
Figure 10 is the high-level schematic functional block diagram of surge elimination unit first embodiment in Fig. 9；
Figure 11 is the high-level schematic functional block diagram of surge elimination unit second embodiment in Fig. 9；
Figure 12 is the high-level schematic functional block diagram of surge elimination unit 3rd embodiment in Fig. 9.
Accompanying drawing marks explanation：
10th, acquisition module；20th, judge module；30th, surge control module；21st, assert unit；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.
Specific embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase
Mutually combine.Below with reference to the accompanying drawings and in conjunction with the embodiments describing the present invention in detail.
With reference to Fig. 1, the preferred embodiments of the present invention provide a kind of aero gas turbine engine surge controlling method, bag
Include step：
Step S100, acquisition combustion chamber inlet pressure and high pressure rotor rotation speed change amount.
The combustion chamber inlet pressure (P3) and velocity sensor that electronic controller collection pressure sensor sends is passed
The high pressure rotor rotating speed brought, is turned with the combustion chamber inlet pressure (P3) and high pressure rotor that obtain aero gas turbine engine
Fast variable quantity (NHDot).
Step S200, the combustion chamber inlet pressure according to obtaining, high pressure rotor rotation speed change amount and default surge inspection
Strategy is surveyed, the surge condition of aero gas turbine engine is judged.
Electronic controller according to obtain combustion chamber inlet pressure (P3), high pressure rotor rotation speed change amount (NHDot) and
Default surge detection strategy, judges the surge condition of aero gas turbine engine, wherein, it is set with surge detection strategy
Two conditions, think that if following two conditions are provided simultaneously with aero gas turbine engine occurs surge：
a)A≥A0；Wherein,A0 is the corresponding pulsating quantity of surge critical point and the ratio of average magnitude, and A0 takes
15.625% (being set with specific reference to the type of aero gas turbine engine), the average magnitude of P3 signals is U1, pulsating quantity
For U2.
B) rotary speed threshold value of the high pressure rotor rotation speed change amount (NHDot) more than setting, wherein, as shown in table 1, rotary speed threshold value
It is the interpolation table with regard to 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
The surge condition of the aero gas turbine engine that step S300, foundation are 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 control in terms of flow and igniting, disappear in time and breathe heavily, the generation of aviation accident can be avoided.
The aero gas turbine engine surge controlling method that the present embodiment is provided, by the combustion chamber inlet-pressure for obtaining
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 the aero gas turbine engine judged, surge control is carried out to aero gas turbine engine,
Surge detection high precision, disappearing, it is good to breathe heavily effect, can be prevented effectively from aviation accident generation.
As shown in Fig. 2 Fig. 2 is the flow process of aero gas turbine engine surge controlling method second embodiment of the present invention showing
It is intended to, on the basis of first embodiment, the aero gas turbine engine surge controlling method that second embodiment is provided, step
S200 includes：
If step S200A, the pulsating quantity ratio of the combustion chamber inlet pressure for obtaining are critical more than or equal to the surge of setting
Pulsating quantity ratio and high pressure rotor rotation speed change amount at point exceedes the rotating speed threshold values of setting, then assert that aviation gas turbine is sent out
There is surge in motivation；Wherein, the pulsating quantity ratio at surge critical point for setting as the corresponding pulsating quantity of surge critical point with it is flat
The ratio measured；Interpolation table of the rotating speed threshold values for setting as both local atmospheric pressure and normal atmospheric pressure ratio；And
The pulsating quantity ratio of combustion chamber inlet pressure is：
Wherein, pulsating quantity ratios of the A for combustion chamber inlet pressure, 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 detection aero gas turbine engine, surge detection high precision, disappearing, it is good to breathe heavily effect, can be prevented effectively from aviation accident and send out
It is raw.
As shown in figure 3, Fig. 3 is the flow process of aero gas turbine engine surge controlling method 3rd embodiment of the present invention showing
It is intended to, on the basis of first embodiment, the aero gas turbine engine surge controlling method that 3rd embodiment is provided, step
S300 includes：
If step S300A, detect aero gas turbine engine occur surge, by starting to aviation gas turbine
The compressor bleed air of machine, fuel flow and igniter fire control effectively until surge is eliminated.
If electronic controller detects aero gas turbine engine there is surge, by starting to aviation gas turbine
The compressor bleed air of machine, fuel flow and igniter fire control effectively until surge is eliminated, for example, control 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 is provided, by aero gas turbine engine
Compressor bleed air, fuel flow and igniter fire control effectively until surge is eliminated, disappearing, it is good to breathe heavily effect, can be effective
Aviation accident is avoided to occur.
As shown in figure 4, Fig. 4 is the flow process of aero gas turbine engine surge controlling method fourth embodiment of the present invention showing
It is intended to, on the basis of 3rd embodiment, the aero gas turbine engine surge controlling method that fourth embodiment is provided, 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 to being 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 to aero gas turbine engine carry out being turned on and off controlling with
Eliminate surge.
Electronic controller carries out being turned on and off control to the high-pressure compressor air bleed valve of aero gas turbine engine
To eliminate surge, disappears the high-pressure compressor air bleed valve that be all turned on 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 is provided, is deflated by default low-pressure compressor
The air bleed valve aperture and high-pressure compressor air bleed valve of valve carries out being turned on and off control to eliminate surge, disappears and breathes heavily effect
It is good, aviation accident generation can be prevented effectively from.
As shown in figure 5, Fig. 5 is the flow process of the 5th embodiment of aero gas turbine engine surge controlling method of the present invention showing
It is intended to, on the basis of fourth embodiment, the aero gas turbine engine surge controlling method that the 5th embodiment is provided, step
S300 includes：
Step S330, the speed of service by fuel oil and default step-size factor are fired to the aviation in different motion state
Gas eddy turbine carries out surge control.
The flow control of electronic controller includes：
A, fuel flow during stable state is controlled：Disappear when breathing heavily, slow down fuel oil growth rate, and step-size factor is set to
0.15, otherwise it is set to 0.75.
B, to accelerate when fuel flow be controlled：After acceleration and deceleration voting, by oil-gas ratio when being directly disposed as surge
(wf/P3) calculate fuel feeding.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, oil-gas ratio restraining line fuel flow is obtained.
C, to slow down when fuel flow be controlled：It is quick to reduce fuel oil, and step-size factor is set for 0.75.
The aero gas turbine engine surge controlling method that the present embodiment is provided, by the flow control to electronic controller
, to eliminate surge, disappearing, it is good to breathe heavily effect for system, can be prevented effectively from aviation accident generation.
As shown in fig. 6, Fig. 6 is the flow process of aero gas turbine engine surge controlling method sixth embodiment of the present invention showing
It is intended to, on the basis of the 5th embodiment, the aero gas turbine engine surge controlling method that sixth embodiment is provided, step
S300 includes：
Step S340, it is controlled to eliminate surge by the duration of ignition to igniter.
Electronic controller when breathing heavily of disappearing controls the duration of ignition of two igniters and is 5S.
The aero gas turbine engine surge controlling method that the present embodiment is provided, by the duration of ignition to igniter
It is controlled to eliminate surge, disappearing, it is good to breathe heavily effect, aviation accident generation can be prevented effectively from.
As shown in fig. 7, the present invention also provides a kind of electronic controller for aero gas turbine engine, including acquisition
Module 10, for obtaining combustion chamber inlet pressure and high pressure rotor rotation speed change amount；Judge module 20, for according to the combustion for obtaining
Room inlet pressure, high pressure rotor rotation speed change amount and default surge detection strategy are burnt, aero gas turbine engine is judged
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 combustion chamber inlet pressure (P3) that sends of collection pressure sensor of acquisition module 10 of electronic controller and
The high pressure rotor rotating speed that velocity sensor sends, to obtain the combustion chamber inlet pressure (P3) of aero gas turbine engine
With high pressure rotor rotation speed change amount (NHDot).
The judge module 20 of electronic controller is according to the combustion chamber inlet pressure (P3), high pressure rotor rotation speed change amount for obtaining
(NHDot) and default surge detection strategy, judge the surge condition of aero gas turbine engine, wherein, surge detection
Two conditions are set with strategy, think that aero gas turbine engine occurs surge if following two conditions are provided simultaneously with：
a)A≥A0；Wherein,A0 is the corresponding pulsating quantity of surge critical point and the ratio of average magnitude, and A0 takes
15.625% (being set with specific reference to the type of aero gas turbine engine), the average magnitude of P3 signals is U1, pulsating quantity
For U2.
B) rotary speed threshold value of the high pressure rotor rotation speed change amount (NHDot) more than setting, wherein, as shown in table 1, rotary speed threshold value
It is the interpolation table with regard to 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 control in terms of compressor bleed air, fuel flow and igniting, disappear in time and breathe heavily, the generation of aviation accident can be avoided.
The electronic controller for aero gas turbine engine that the present embodiment is provided, by the combustion chamber import for obtaining
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 of the aero gas turbine engine judged, surge control is carried out to aero gas turbine engine
System, surge detection high precision, disappearing, it is good to breathe heavily effect, can be prevented effectively from aviation accident generation.
As shown in figure 8, Fig. 8 is the high-level schematic functional block diagram of one preferred embodiment of judge module in Fig. 7, in the present embodiment
In, judge module 20 includes assert unit 21, if assert the pulsating quantity ratio of the combustion chamber inlet pressure that unit 21 is used to obtain
Exceed the rotating speed of setting more than or equal to the pulsating quantity ratio and high pressure rotor rotation speed change amount at the surge critical point of setting
Threshold values, then assert that aero gas turbine engine occurs surge；Wherein, the pulsating quantity ratio at surge critical point for setting is to breathe heavily
The ratio of the corresponding pulsating quantity of critical point of shaking and average magnitude；The rotating speed threshold values for setting 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, pulsating quantity ratios of the A for combustion chamber inlet pressure, 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 is provided, by default surge detection plan
Slightly detecting the surge of aero gas turbine engine, surge detection high precision, disappearing, it is good to breathe heavily effect, can be prevented effectively from aviation accident
Occur.
As shown in figure 9, Fig. 9 is the high-level schematic functional block diagram of one preferred embodiment of judge module in Fig. 7, in the present embodiment
In, surge control module 30 includes that surge eliminates unit 31, if surge eliminates unit 31 and is used to detect aviation gas turbine
There is surge in motivation, then entered by the compressor bleed air to aero gas turbine engine, fuel flow and igniter fire
Row effective control is until surge is eliminated.
If the surge of electronic controller eliminates unit 31 and detects aero gas turbine engine generation surge, by right
The compressor bleed air of aero gas turbine engine, fuel flow and igniter fire control effectively until surge disappears
Remove, for example, control the air bleed valve discharge quantity of 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 is provided, by sending out to aviation gas turbine
The compressor bleed air of motivation, fuel flow and igniter fire control effectively until surge is eliminated, and disappearing, it is good to breathe heavily effect, can
It is prevented effectively from aviation accident generation.
As shown in Figure 10, Figure 10 is the high-level schematic functional block diagram of surge elimination unit first embodiment in Fig. 9, in this enforcement
In example, surge 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 controls subelement 312 for being turned on and off to 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 of electronic controller controls subelement 311 by 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, slows down
When surge.
The high-pressure compressor air bleed valve control high pressure of the subelement 312 to aero gas turbine engine of electronic controller
Compressor bleed air valve carries out being turned on and off control to eliminate surge, and disappears the high-pressure compressor air bleed valve that be all turned on when breathing heavily；
And high-pressure compressor air bleed valve is then closed in remaining time.
The electronic controller for aero gas turbine engine that the present embodiment is provided, by default low-pressure compressor
The air bleed valve aperture and high-pressure compressor air bleed valve of air bleed valve carries out being turned on and off control to eliminate surge, disappears and breathes heavily
Effect is good, can be prevented effectively from aviation accident generation.
As shown in figure 11, Figure 11 is the high-level schematic functional block diagram of surge elimination unit second embodiment in Fig. 9, in this enforcement
In example, surge eliminates unit 31 includes fuel flow control subelement 313, and fuel flow control subelement 313 is used for by combustion
The speed of service and default step-size factor of oil carries 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：
A, fuel flow during stable state is controlled：Disappear when breathing heavily, slow down fuel oil growth rate, and step-size factor is set to
0.15, otherwise it is set to 0.75.
B, to accelerate when fuel flow be controlled：After acceleration and deceleration voting, by oil-gas ratio when being directly disposed as surge
(wf/P3) calculate fuel feeding.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, oil-gas ratio restraining line fuel flow is obtained.
C, to slow down when fuel flow be controlled：It is quick to reduce fuel oil, and step-size factor is set for 0.75.
The electronic controller for aero gas turbine engine that the present embodiment is provided, by the stream to electronic controller
To eliminate surge, disappearing, it is good to breathe heavily effect for amount control, can be prevented effectively from aviation accident generation.
As shown in figure 12, Figure 12 is the high-level schematic functional block diagram of surge elimination unit 3rd embodiment in Fig. 9, in this enforcement
In example, surge eliminates unit 31 includes igniter fire control subelement 314, and igniter fire control subelement 314 is used to lead to
Spending the duration of ignition to igniter is controlled to eliminate surge.
The igniter fire control subelement 314 of electronic controller when breathing heavily of disappearing controls duration of ignition of two igniters and is
5S。
The electronic controller for aero gas turbine engine that the present embodiment is provided, by the igniting to igniter
Time is controlled to eliminate surge, and disappearing, it is good to breathe heavily effect, can be prevented effectively from aviation accident generation.
The preferred embodiments of the present invention are the foregoing is only, the present invention is not limited to, for the skill of this area
For art personnel, the present invention can have various modifications and variations.It is all within the spirit and principles in the present invention, made any repair
Change, equivalent, improvement etc., should be included within the scope of the present invention.
Claims (10)
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, the high pressure rotor rotation speed change amount and default surge detection plan that obtain
Slightly, judge the surge condition of the aero gas turbine engine；
According to the surge condition of the aero gas turbine engine judged, the aero gas turbine engine is carried out
Surge is controlled.
2. aero gas turbine engine surge controlling method according to claim 1, it is characterised in that
It is described according to the combustion chamber inlet pressure for obtaining, the high pressure rotor rotation speed change amount and default surge detection
The step of strategy, surge condition for judging the aero gas turbine engine, includes：
If the pulsating quantity ratio of the combustion chamber inlet pressure for obtaining is more than or equal to the pulsation at the surge critical point of setting
Amount ratio and the high pressure rotor rotation speed change amount exceed the rotating speed threshold values of setting, then assert that the aviation gas turbine starts
There is surge in machine；Wherein, the pulsating quantity ratio at the surge critical point for setting as the corresponding pulsating quantity of surge critical point with
The ratio of average magnitude；Interpolation table of the rotating speed threshold values for setting as both local atmospheric pressure and normal atmospheric pressure ratio；
And
The pulsating quantity ratio of the combustion chamber inlet pressure is：
Wherein, pulsating quantity ratios of the A for combustion chamber inlet pressure, U1For the average magnitude of combustion chamber inlet pressure signal, U2For burning
The pulsating quantity of room inlet pressure signal.
3. aero gas turbine engine surge controlling method according to claim 1, it is characterised in that
The surge condition of the aero gas turbine engine that the foundation is judged, to the aero gas turbine engine
Carrying out the step of surge is controlled includes：
If detecting the aero gas turbine engine there is surge, by the pressure to the aero gas turbine engine
Mechanism of qi is deflated, fuel flow and igniter fire control effectively up to surge and eliminate.
4. aero gas turbine engine surge controlling method according to claim 3, it is characterised in that
The step of compressor bleed air by the aero gas turbine engine control effectively includes：
By the air bleed valve aperture of default low-pressure compressor air bleed valve to the aviation combustion in different motion state
The surge of gas eddy turbine is controlled；
Carry out being turned on and off control to eliminate surge to the high-pressure compressor air bleed valve of the aero gas turbine engine.
5. aero gas turbine engine surge controlling method according to claim 3, it is characterised in that
The step of fuel flow by the aero gas turbine engine control effectively 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.
6. a kind of electronic controller for aero gas turbine engine, it is characterised in that include：
Acquisition module (10), for obtaining combustion chamber inlet pressure and high pressure rotor rotation speed change amount；
Judge module (20), for according to obtain the combustion chamber inlet pressure, the high pressure rotor rotation speed change amount and
Default surge detection strategy, judges 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.
7. the electronic controller for aero gas turbine engine according to claim 6, it is characterised in that
The judge module (20) includes identification unit (21),
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
There is surge in the aero gas turbine engine；Wherein, the pulsating quantity ratio at the surge critical point for setting is as surge
The ratio of the corresponding pulsating quantity of critical point and average magnitude；The rotating speed threshold values for setting 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：
Wherein, pulsating quantity ratios of the A for combustion chamber inlet pressure, U1For the average magnitude of combustion chamber inlet pressure signal, U2For burning
The pulsating quantity of room inlet pressure signal.
8. the electronic controller for aero gas turbine engine according to claim 6, it is characterised in that
The surge control module (30) eliminates unit (31) including surge,
The surge eliminates unit (31), if there is surge for detecting the aero gas turbine engine, by right
The compressor bleed air of the aero gas turbine engine, fuel flow and igniter fire control effectively until surge
Eliminate.
9. the electronic controller for aero gas turbine engine according to claim 8, it is characterised in that
The surge eliminates unit (31) and deflates including low-pressure compressor air bleed valve control subelement (311) and high-pressure compressor
Valve control subelement (312),
Low-pressure compressor air bleed valve control subelement (311), 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 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.
10. the electronic controller for aero gas turbine engine according to claim 8, it is characterised in that
The surge eliminates unit (31) including fuel flow control subelement (313),
Fuel flow control subelement (313), for passing through the speed of service and default step-size factor of fuel oil to being in
The aero gas turbine engine of different motion state carries out surge control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610992726.7A CN106523163B (en) | 2016-11-11 | 2016-11-11 | Aero gas turbine engine surge controlling method and electronic controller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610992726.7A CN106523163B (en) | 2016-11-11 | 2016-11-11 | Aero gas turbine engine surge controlling method and electronic controller |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106523163A true CN106523163A (en) | 2017-03-22 |
| CN106523163B CN106523163B (en) | 2018-03-02 |
Family
ID=58351054
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610992726.7A Active CN106523163B (en) | 2016-11-11 | 2016-11-11 | Aero gas turbine engine surge controlling method and electronic controller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106523163B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108825391A (en) * | 2018-07-10 | 2018-11-16 | 潍柴西港新能源动力有限公司 | Improve the device and its response method of natural gas engine transient response |
| 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 |
| CN110657031A (en) * | 2019-09-30 | 2020-01-07 | 山东超越数控电子股份有限公司 | Method for identifying surge of aircraft engine |
| CN110735669A (en) * | 2019-10-08 | 2020-01-31 | 中国航发沈阳发动机研究所 | Method and device for judging rotating stall of aviation gas turbine engine |
| CN112594062A (en) * | 2020-11-13 | 2021-04-02 | 南京航空航天大学 | Simulation method for surge detection and surge elimination control verification |
| 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 |
| CN114060151A (en) * | 2020-07-30 | 2022-02-18 | 中国航发商用航空发动机有限责任公司 | Control method and device for preventing engine from breathing and asthma |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1508970A (en) * | 1975-11-19 | 1978-04-26 | United Technologies Corp | Stall detector and method for detecting stall in a gas turbine engine |
| US4118926A (en) * | 1977-02-28 | 1978-10-10 | United Technologies Corporation | Automatic stall recovery system |
| US4991389A (en) * | 1989-04-21 | 1991-02-12 | United Technologies Corporation | Bleed modulation for transient engine operation |
| CN1052170A (en) * | 1989-05-30 | 1991-06-12 | 联合工艺公司 | Acceleration control with gas turbine of pressure loss in piping compensation |
| US6269627B1 (en) * | 1998-12-16 | 2001-08-07 | United Technologies Corporation | Rapid thrust response control logic for shaft-driven lift fan STOVL engine |
-
2016
- 2016-11-11 CN CN201610992726.7A patent/CN106523163B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1508970A (en) * | 1975-11-19 | 1978-04-26 | United Technologies Corp | Stall detector and method for detecting stall in a gas turbine engine |
| US4118926A (en) * | 1977-02-28 | 1978-10-10 | United Technologies Corporation | Automatic stall recovery system |
| US4991389A (en) * | 1989-04-21 | 1991-02-12 | United Technologies Corporation | Bleed modulation for transient engine operation |
| CN1052170A (en) * | 1989-05-30 | 1991-06-12 | 联合工艺公司 | Acceleration control with gas turbine of pressure loss in piping compensation |
| US6269627B1 (en) * | 1998-12-16 | 2001-08-07 | United Technologies Corporation | Rapid thrust response control logic for shaft-driven lift fan STOVL engine |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108825391B (en) * | 2018-07-10 | 2023-10-20 | 潍柴西港新能源动力有限公司 | Device for improving transient response of natural gas engine and response method thereof |
| CN108825391A (en) * | 2018-07-10 | 2018-11-16 | 潍柴西港新能源动力有限公司 | Improve the device and its response method of natural gas engine transient response |
| 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 |
| 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 |
| CN110657031A (en) * | 2019-09-30 | 2020-01-07 | 山东超越数控电子股份有限公司 | Method for identifying surge of aircraft engine |
| CN110735669A (en) * | 2019-10-08 | 2020-01-31 | 中国航发沈阳发动机研究所 | Method and device for judging rotating stall of aviation gas turbine 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 |
| CN114060151A (en) * | 2020-07-30 | 2022-02-18 | 中国航发商用航空发动机有限责任公司 | Control method and device for preventing engine from breathing and asthma |
| CN114060151B (en) * | 2020-07-30 | 2023-05-26 | 中国航发商用航空发动机有限责任公司 | Control method and device for relieving asthma and preventing asthma of engine |
| CN112594062A (en) * | 2020-11-13 | 2021-04-02 | 南京航空航天大学 | Simulation method for surge detection and surge elimination control verification |
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106523163B (en) | 2018-03-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106523163B (en) | Aero gas turbine engine surge controlling method and electronic controller | |
| CN106321252B (en) | The starting process fuel oil control method and system of a kind of aero-engine | |
| CA2348342C (en) | Surge detection system of gas turbine aeroengine | |
| US4622808A (en) | Surge/stall cessation detection system | |
| CN105822406B (en) | Internal combustion engine | |
| US20070245746A1 (en) | Methods and systems for detecting rotor assembly speed oscillation in turbine engines | |
| EP0590829B1 (en) | Apparatus and method of automatic NOx control for a gas turbine | |
| JP2016205371A (en) | Ignition detection device of gas turbine engine for aircraft | |
| US11667392B2 (en) | Method and system for operating a rotorcraft engine | |
| EP1462634A2 (en) | Acceleration control in multispool gas turbine engine | |
| US7599767B2 (en) | Control apparatus and control method for aircraft | |
| US9915166B2 (en) | Gas turbine and method for operating the gas turbine | |
| JP6633962B2 (en) | Aircraft gas turbine engine controller | |
| EP3309373B1 (en) | Integrated starter for aerial vehicle | |
| EP3309374B1 (en) | Starter issue detection | |
| CN105971737B (en) | A kind of sequential control method for improving punching engine ignition success rate | |
| EP0905358B1 (en) | Control Method | |
| JP4705732B2 (en) | Surge detector for aircraft gas turbine engine | |
| CN209586526U (en) | The automatically controlled turbocharger of motor overspeed protection system in plateau | |
| CN109578097A (en) | A kind of control system and control method proposing effect based on spraying combined cycle unit | |
| JP4430220B2 (en) | Control device for aircraft gas turbine engine | |
| CN105917104B (en) | Engine | |
| US20140260287A1 (en) | Gas turbine firing temperature optimization based on sulfur content of fuel supply | |
| CN114893300B (en) | Parameter control pressure parameter judging method and redundancy control method for small turbofan engine | |
| JP2009228652A (en) | Control device for gas turbine engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |