CN107100744B - A kind of aero-engine fuel metering system improvement strategy and its controller design method - Google Patents
A kind of aero-engine fuel metering system improvement strategy and its controller design method Download PDFInfo
- Publication number
- CN107100744B CN107100744B CN201710397511.5A CN201710397511A CN107100744B CN 107100744 B CN107100744 B CN 107100744B CN 201710397511 A CN201710397511 A CN 201710397511A CN 107100744 B CN107100744 B CN 107100744B
- Authority
- CN
- China
- Prior art keywords
- pressure difference
- fuel
- metering
- metering valve
- flow
- 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.)
- Active
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 114
- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000013461 design Methods 0.000 title claims abstract description 23
- 230000006872 improvement Effects 0.000 title claims abstract description 8
- 230000008859 change Effects 0.000 claims abstract description 30
- 230000009977 dual effect Effects 0.000 claims abstract description 19
- 239000003921 oil Substances 0.000 claims description 27
- 239000000295 fuel oil Substances 0.000 claims description 21
- 238000006073 displacement reaction Methods 0.000 claims description 20
- 230000003134 recirculating effect Effects 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 3
- 239000011148 porous material Substances 0.000 claims description 2
- 238000005259 measurement Methods 0.000 abstract description 6
- 238000010276 construction Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 7
- 230000035945 sensitivity Effects 0.000 description 6
- 238000004088 simulation Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 101000609957 Homo sapiens PTB-containing, cubilin and LRP1-interacting protein Proteins 0.000 description 1
- 241000145637 Lepturus Species 0.000 description 1
- 101150109471 PID2 gene Proteins 0.000 description 1
- 102100039157 PTB-containing, cubilin and LRP1-interacting protein Human genes 0.000 description 1
- 241001494479 Pecora Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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
- F02C9/26—Control of fuel supply
- F02C9/38—Control of fuel supply characterised by throttling and returning of fuel to sump
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
- F05D2270/3015—Pressure differential pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/70—Type of control algorithm
- F05D2270/706—Type of control algorithm proportional-integral-differential
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Measuring Volume Flow (AREA)
Abstract
A kind of aero-engine fuel metering system improvement strategy and its controller design method, it is new control variable mode by adjusting pressure difference before and after differential pressure controller modular construction, increase metering valve, traditional level pressure difference flow measurement device is improved to novel change pressure difference fuel-metering device, desired fuel flow is realized by the front and back pressure difference of metering valve and the dual variation method of circulation area；According to becoming pressure difference fuel metering system increase maximum stream flow range and putting forward high-precision demand, propose that the pressure difference use of metering valve has a grade control model, circulation area to use a kind of dual variation method rule of stepless control model.Under aero-engine big flow demand, by suitably increasing pressure difference, the fuel flow of bigger is can get under conditions of current maximum flow area, expands fuel flow and measures range；Under small flow demand, under the conditions of the structure of metering valve type hole is fixed, flow gain is reduced by reducing pressure difference, improves the measuring accuracy of system.
Description
Technical field
The present invention provides a kind of aero-engine fuel metering system improvement strategy and its controller design methods, belong to
Aviation aerospace hydraulic-mechanic system designs and emulation field.
Background technology
The major function of aero-engine fuel metering system is given according to the mission requirements of engine different working condition
Combustion chamber provides the pressurized fuel of different flow, to ensure that engine can be stablized under each state, reliably run.Currently,
Domestic air mail engine fuel metering system is mostly level pressure difference fuel metering structure, using the group of differential pressure controller and metering valve
Conjunction mode ensures that the fuel pressure difference before and after metering valve is constant by differential pressure controller, and then makes the fuel delivery of engine only
Aperture depending on metering valve.With the extension of aero-engine flight envelope, the promotion of performance, engine is to fuel flow
The requirement of range, fuel oil control accuracy and rapidity increasingly improve, in the side such as the weight of fuel control system and Control platform
Face is also proposed more stringent requirement.In particular, very big to big fuel flow and small fuel flow demand difference in engine
In the case of, conventional level pressure difference fuel control system is difficult to meet the response speed under big flow demand and requires and small flow need
Control accuracy requirement under asking.To solve the problems, such as this, this patent proposes that a kind of aero-engine becomes pressure difference fuel metering system and sets
Count thinking and corresponding dual variation method device design method.
Invention content
In order to make aero-engine fuel metering system realize higher precision to fuel flow in the range of flow of bigger
Adjusting, the present invention proposes that a kind of improvement level pressure difference fuel metering system be the method for change pressure difference fuel metering system, and provides
Corresponding dual variation method device layout strategy.
A kind of aero-engine fuel metering system improvement strategy and its controller design method, steps are as follows：
Step 1. design becomes pressure difference fuel-metering device
Based on traditional level pressure difference fuel metering system, differential pressure controller component is adjusted, that is, removes differential pressure valve and only protects
Oil return valve is stayed, and adds the position control channel of an oil return valve, metering valve is controlled by the aperture of oil return valve
The recirculating oil quantity of preceding fuel oil reaches change pressure difference purpose to change pressure difference before and after metering valve, realizes traditional level pressure difference fuel oil meter
Amount device is improved to novel change pressure difference fuel-metering device, then flows through the fuel flow of metering valve by being pressed before and after metering valve
Poor Δ P and circulation area AlIt codetermines；
Step 2. designs novel change pressure difference fuel-metering device control system
On the basis of traditional constant pressure difference control pattern, the pressure difference control variable new as one before and after increase metering valve,
Design one kind is by pressure differential deltap P before and after metering valve and circulation area AlThe novel change pressure difference fuel metering system of dual variation method,
Metering valve current position signal is fed back to electronic controller by the displacement sensor being connected with metering valve, realizes metering valve
Closed-loop control (the reflection fuel flow communication area A of positionl), the pressure sensor of oil circuit will be counted currently before and after metering valve
Fuel pressure signal before and after amount valve feeds back to electronic controller, realizes closed-loop control (the reflection metering of oil return valve position
Pressure differential deltap P before and after valve), double changes which passes through pressure difference before and after metering valve and circulation area
Amount controls to realize the metering of fuel flow；
Step 3. designs the dual variation method rule of novel change pressure difference fuel metering system
Increase maximum stream flow range according to novel change pressure difference fuel metering system and improves the demand of small-flow precise degree, it is double
Pressure differential deltap P, which is used, in Variable Control, before and after metering valve a grade control law, i.e. " small flow-small pressure difference ", " big flow-pressure greatly
The aperture (reflection circulation area) of the principle of grading of difference ", metering valve then uses stepless control law, i.e., by expectation fuel flow
The Q and pressure differential deltap P determined, according to flow equation (1)
In formula：Q --- the fuel flow of metering valve is flowed through,
Cd--- the discharge coefficient of metering valve,
Al--- the circulation area of metering valve,
ρg--- fuel density,
Δ P --- the fuel oil pressure difference before and after metering valve,
Calculate current desired fuel flow communication area Al, then metering valve aperture obtained by metering type pore geometry size, and
The dual variation method rule is realized using pid control algorithm；
Step 4. builds complete novel change pressure difference fuel flowmeter amount system
Combining step 1-3 establishes entire aero-engine and becomes pressure difference fuel flowmeter amount system, according to pressure difference and circulating face
Product dual variation method rule, obtains the corresponding desired locations signal of metering valve and desired pressure differential signal, is obtained by displacement sensor
To the position feed back signal of current metering valve, compared with the desired locations signal of metering valve, by PID controller 1
It calculates, obtains control signal of the electrohydraulic servo valve 1 to metering valve aperture；Metering valve is experienced respectively by two pressure sensors
Forward and backward fuel pressure obtains the front and back Pressure difference feedback signal of metering valve, and compared with the desired pressure differential signal of metering valve
Compared with by the calculating of PID controller 2, obtaining control signal of the electrohydraulic servo valve 2 to oil return valve opening, and then pass through control
Recirculating oil quantity before metering valve finally obtains fuel oil stream required under engine different working condition to realize desired pressure difference
Amount.
Beneficial effects of the present invention：A kind of aero-engine fuel-metering device improvement strategy of present invention proposition and its control
Device design method changes the fuel oil pressure difference before and after metering valve, the change pressure difference fuel oil according to different expectation fuel flow ranges
Measurement technology can ensure the measuring accuracy of fuel flow while expanding fuel flow metering range.When big flow demand,
By suitably increasing pressure difference, the fuel flow of bigger is obtained under conditions of current maximum flow area, that is, expands fuel oil stream
Measures range is measured, while the flow gain of bigger will also make fuel control system have faster response speed；Small flow demand
When, under the conditions of metering valve type hole structure is fixed, flow gain is reduced by reducing pressure difference, is so as to improve
The measuring accuracy of system.
Description of the drawings
Fig. 1 is certain traditional type level pressure difference fuel-metering device structure chart.
Fig. 2 is novel change pressure difference fuel-metering device structure chart.
Fig. 3 is level pressure difference fuel metering system control structure block diagram.
Fig. 4 is novel change pressure difference fuel metering system control structure block diagram.
Fig. 5 is the pressure difference and circulation area dual variation method rule schematic diagram for becoming pressure difference fuel metering system.
Fig. 6 is novel change pressure difference fuel-metering device and its control system schematic diagram.
Fig. 7 is level pressure difference and change pressure difference fuel metering system pressure difference variation track comparison diagram.
Fig. 8 is level pressure difference and change pressure difference fuel metering system changes in flow rate track comparison diagram.
Fig. 9 is level pressure difference and becomes the Sensitivity comparison figure (big flow) of pressure difference fuel metering system.
Figure 10 is level pressure difference and becomes the Sensitivity comparison figure (small flow) of pressure difference fuel metering system.
Figure 11 is level pressure difference and becomes the measurement error comparison diagram (small flow) of pressure difference fuel metering system.
Specific implementation mode
Below in conjunction with attached drawing and technical solution, the specific implementation mode that further illustrates the present invention.
The present embodiment is fuel-metering device improved method and its Control System Design of a kind of Aviation engine.Tool
Steps are as follows for body detailed design：
Step 1. design becomes pressure difference fuel-metering device structure.
Certain traditional type level pressure difference fuel-metering device is as shown in Figure 1, wherein differential pressure valve, oil return valve and safety valve
Collectively constituted differential pressure controller, effect be to maintain flow through metering valve front and back pressure differential deltap P it is constant, to make fuel flow
With the circulation area A of metering valvelIn monotropic function relationship.On this architecture basics, it is improved to become pressure difference fuel metering
Device adjusts differential pressure controller component, that is, removes differential pressure valve and only retain oil return valve structure, and adds an oil return valve
Position control channel, by adjust oil return valve aperture control metering valve before fuel oil recirculating oil quantity, to adjust metering
Pressure difference before and after valve achievees the purpose that " becoming pressure difference ", and the novel change pressure difference fuel metering system structure as shown in Fig. 2, flow at this time
The fuel flow of metering valve is crossed by pressure differential deltap P before and after metering valve and circulation area AlIt codetermines.
Step 2. designs novel change pressure difference fuel-metering device control system framework.
For traditional level pressure difference fuel-metering device, control system frame is as shown in figure 3, supply engine combustion chamber
Fuel flow is to be cooperated to complete by electronic controller ECU and fuel-metering device, electronic controller ECU experience engine into
The working status parameters such as mouthful temperature, compressor delivery pressure and engine speed, and then be calculated and engine it is expected fuel oil
The desired locations signal of the corresponding metering valve of flow；By compared with metering valve position feed back signal, calculating and defeated
Go out the control signal of electrohydraulic servo valve；And then the aperture of metering valve is controlled by electrohydraulic servo valve, to obtain engine difference
Fuel flow needed for working condition.The displacement transducer LVDT being connected with metering valve is anti-by metering valve current position signal
It is fed to electronic controller ECU, realizes the closed-loop control of metering valve position.
On the basis of above-mentioned traditional constant pressure difference control pattern, it is used as one newly by pressure differential deltap P before and after increasing metering valve
Control variable, and then design one kind by pressure differential deltap P and circulation area AlThe novel change pressure difference fuel metering system of dual variation method
System.Become pressure difference fuel metering Control system architecture as shown in figure 4, the LVDT displacement sensors being connected with metering valve live metering
Door current position signal feeds back to electronic controller ECU, realizes closed-loop control (the reflection circulation area A of metering valve positionl)；
Fuel pressure signal before and after current metering valve is fed back to electronics by the pressure sensor mounted on oil circuit before and after metering valve
Controller ECU realizes the closed-loop control (reflection metering valve pressure differential deltap P) of oil return valve position.The novel change pressure difference fuel oil meter
Amount system realizes the metering of fuel flow by pressure difference before and after metering valve and the dual variation method of circulation area.
Step 3. designs the dual variation method rule of novel change pressure difference fuel metering system and algorithm is realized
By step 2 it is found that become pressure difference fuel metering system by metering valve front and back pressure differential deltap P and metering valve circulation
Area AlDual variation method realize, and corresponding control law determine the two control variables and desired fuel flow it
Between relationship, dual variation method rule principle in this patent as shown in figure 5, the wherein pressure difference of metering valve using there is grade to control
Pattern；The aperture of metering valve then uses the pattern of stepless control.Such control model can be to avoid in the essence for realizing fuel oil
Really when control, pressure difference control interfering with each other and being crosslinked with the two control module of flow control.
(1) principle of grading of pressure differential deltap P and basic control law
According to the demand for it is expected to become pressure difference fuel metering system increase maximum stream flow range and raising small-flow precise degree, adopt
With the pressure difference classification principle of " small flow-small pressure difference ", " the big pressure difference of big flow-".For the present embodiment, according to certain type aeroplane engine
The factors such as the range of flow requirement of machine fuel-metering device, type hole size can get after the experiment of a large amount of pressure difference mechanism simulation
Can ensure pressure difference mechanism normal work metering valve before and after pressure difference variation range；Then according to corresponding fuel metering essence
Degree requires, and is segmented to fuel flow range, and determines the pressure difference of each flow section successively.It is final true through iterating
It is fixed that three class control is carried out to pressure differential deltap P：
Small fuel flow section (100~1000) kg/h：Use minimum differntial pressure Δ Pmin；
Intermediate fuel flow section (1000~10000) kg/h：Use intermediate pressure differential deltap Pmidd；
Big fuel flow section (>10000)kg/h：Use maximum differential pressure Δ Pmax。
Linking between three pressure difference-flow sections is equivalent to the interference signal of step form according to the form of jumping characteristic
The change in location of input, oil return valve and metering valve can be relatively more violent, and corresponding fuel metering output also has distortion, unfavorable
In the even running of system.Therefore, between different fuel flow sections when transition, the expectation displacement of metering valve should continuously become
Change, it is final to determine that the pressure difference classification situation of the present embodiment is as follows：
Small fuel flow section (100~900) kg/h：Use minimum differntial pressure Δ Pmin；
Changeover portion 1 (900~2000) kg/h：Pressure difference is by Δ PminRamp to Δ Pmidd；
Intermediate fuel flow section (2000~9000) kg/h：Use intermediate pressure differential deltap Pmidd；
Changeover portion 2 (9000~15000) kg/h：Pressure difference is by Δ PmiddRamp to Δ Pmax；
Big fuel flow section (>15000)kg/h：Use maximum differential pressure Δ Pmax。
(2) circulation area AlControl form
The circulation area A of metering valvelIt is directly to be embodied by the displacement L of valve (spool).Therefore, displacement L is straight
Control variable is connect, relationship between the two is determined by the geometric dimension of metering type hole.
For the expectation fuel flow signal Q that electronic controller ECU gives, before should determining the metering valve first
The grade of pressure difference afterwards determines the desired pressure differential value Δ P for being adapted to present flow rate range；Then according to desired fuel flow and really
Fixed pressure difference determines the expectation circulation area A of current metering valvel, Main Basiss are the flow equations of metering valve
Formula：
In formula：Q --- flow through the fuel flow of metering valve；
Cd--- the discharge coefficient of metering valve；
The circulation area of Al --- metering valve；
ρg--- fuel density；
Δ P --- the fuel oil pressure difference before and after metering valve.
To realize control law, this patent is using pid control algorithm to becoming the metering valve in pressure difference fuel-metering device
Position control loop and pressure difference control loop carried out the design of controller.This is because pid algorithm is simple, there is robustness
Well, the advantages that reliability is high, easy to adjust can substantially meet Engineering Control requirement.
Step 4. integrated control law and control algolithm build complete change pressure difference fuel flowmeter amount system.
Combining step 1-3 establishes novel aero-engine and becomes pressure difference fuel flowmeter amount device and its control system, former
Reason is as shown in Figure 6.According to pressure difference and circulation area dual variation method rule, obtain the corresponding desired locations signal of metering valve and
Desired pressure differential signal.The position feed back signal of current metering valve is obtained by displacement transducer LVDT, the expectation with metering valve
Position signal compares, and by the calculating of controller PID1, obtains control signal of the electrohydraulic servo valve 1 to metering valve aperture；
The forward and backward fuel pressure of metering valve is experienced respectively by two pressure sensors, obtains the front and back Pressure difference feedback letter of metering valve
Number, and compared with the desired pressure differential signal of metering valve, by the calculating of controller PID2, electrohydraulic servo valve 2 is obtained to returning
The control signal of oil valve aperture, and then by the recirculating oil quantity before control metering valve to realize desired pressure difference, it is final to obtain
Fuel flow needed under to engine different working condition.
In order to illustrate the effect of pressure difference fuel-metering device and its control system is become in the present embodiment, it is based on AMESim softwares
Progress level pressure is poor respectively, becomes pressure difference fuel-metering device and its modeling and simulation of control system, by two groups of simulation examples, comes
Show the advantage of novel change pressure difference fuel metering system in the present invention.
(1) the big fuel flow demand of aero-engine
Simulation parameter is set, metering valve displacement is made to vary continuously to maximum value by minimum value, Fig. 7 and Fig. 8 are meter respectively
Measure the situation of change and fuel flow variation track of the pressure difference before and after valve.As shown in Figure 7, level pressure difference fuel-metering device
Fuel oil pressure difference is constant before and after full flow section keeps metering valve；Become pressure difference fuel-metering device then according to different fuel oil stream
Section is measured, the fuel oil pressure difference before and after metering valve is synchronized and is adjusted correspondingly.As shown in Figure 8, with metering valve displacement
Constantly increase, the output fuel flow of fuel-metering device also incrementally increases；Level pressure difference fuel-metering device is at maximum displacement
(maximum flow area) corresponding fuel flow output is 100%；Become pressure difference fuel-metering device (max-flow at maximum displacement
Logical area) fuel flow output that 130% can be reached, it realizes and increases combustion in the case where metering valve circulation area is constant
The purpose of oil stream amount.Fig. 9 is the sensitivity curve of the fuel-metering device in the case of big fuel flow output, becomes pressure difference fuel oil meter
Measure device to the flow gain of displacement higher than level pressure difference fuel-metering device to the flow gain of displacement, i.e. the former sensitivity more
Height, therefore become pressure difference fuel-metering device with faster response speed.
(2) the small fuel flow demand of aero-engine
Simulation parameter is set, so that metering valve displacement is changed in initial segment, i.e., fuel flow is in small flow segment limit
(100~1000kg/h), Figure 10 and Figure 11 are sensitivity curve and measurement error song in the case of small fuel flow output respectively
Line.When metering valve is in initial thin tail sheep section (0~6mm), under the conditions of metering valve type hole is fixed, become pressure difference fuel oil meter
It measures device and level pressure difference fuel-metering device is less than to the flow gain of displacement to the flow gain of displacement, sensitivity is low, that is, increases
When identical displacement, the flow for becoming pressure difference fuel-metering device increases slower, this is more conducive to realize that fuel flow is more accurate
Adjusting；As shown in Figure 11, in small fuel flow section (100~900kg/h), become the measurement error ratio of pressure difference fuel-metering device
The measurement error of level pressure difference fuel-metering device is small, has higher measuring accuracy.
Claims (1)
1. a kind of aero-engine fuel metering system improvement strategy, which is characterized in that steps are as follows：
Step 1. design becomes pressure difference fuel-metering device
Based on traditional level pressure difference fuel metering system, removes differential pressure valve and only retain oil return valve, and an additional oil return is lived
The position control channel of door adjusts the recirculating oil quantity of fuel oil before metering valve, to change by controlling the aperture of oil return valve
Pressure difference, which reaches, before and after metering valve becomes pressure difference purpose, realizes that traditional level pressure difference fuel-metering device is improved to become pressure difference fuel oil meter
Device is measured, then flows through the fuel flow of metering valve by pressure differential deltap P before and after metering valve and circulation area AlIt codetermines；
Step 2. design becomes pressure difference fuel-metering device control system
On the basis of traditional constant pressure difference control pattern, the pressure difference control variable new as one, design before and after increase metering valve
One kind is by pressure differential deltap P before and after metering valve and circulation area AlThe change pressure difference fuel metering system of dual variation method is lived with metering
Metering valve current position signal is fed back to electronic controller by the connected displacement sensor of door, realizes closing for metering valve position
Ring controls, and the pressure sensor mounted on oil circuit before and after metering valve feeds back the fuel pressure signal before and after current metering valve
To electronic controller, the closed-loop control of oil return valve position is realized, before and after the change pressure difference fuel metering system is by metering valve
Pressure difference and the dual variation method of circulation area realize the metering of fuel flow；
Step 3. design becomes the dual variation method rule of pressure difference fuel metering system
Increase maximum stream flow range and the demand of raising small-flow precise degree, dual variation method according to pressure difference fuel metering system is become
In, pressure differential deltap P, which is used, before and after metering valve a grade control law, i.e. point of " small flow-small pressure difference ", " the big pressure difference of big flow-"
The aperture of grade principle, metering valve then uses stepless control law, i.e., by expectation fuel flow Q and the pressure differential deltap P determined, foundation
Flow equation (1)
In formula：Q --- the fuel flow of metering valve is flowed through,
Cd--- the discharge coefficient of metering valve,
Al--- the circulation area of metering valve,
ρg--- fuel density,
Δ P --- the fuel oil pressure difference before and after metering valve,
Calculate current desired fuel flow communication area Al, then metering valve aperture obtained by metering type pore geometry size, and use
Pid control algorithm realizes the dual variation method rule；
Step 4. builds complete change pressure difference fuel flowmeter amount system
Combining step 1-3 establishes entire aero-engine and becomes pressure difference fuel flowmeter amount system, double according to pressure difference and circulation area
Variable Control rule obtains the corresponding desired locations signal of metering valve and desired pressure differential signal, is worked as by displacement sensor
The position feed back signal of preceding metering valve, compared with the desired locations signal of metering valve, by the first PID controller (1)
Calculating, obtain control signal of the first electrohydraulic servo valve (1) to metering valve aperture；Experienced respectively by two pressure sensors
The forward and backward fuel pressure of metering valve, obtains the front and back Pressure difference feedback signal of metering valve, and with the desired pressure differential of metering valve
Signal compares, and by the calculating of the second PID controller (2), obtains control of the second electrohydraulic servo valve (2) to oil return valve opening
Signal processed, and then engine difference work is finally obtained to realize desired pressure difference by the recirculating oil quantity before control metering valve
Fuel flow needed for making under state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710397511.5A CN107100744B (en) | 2017-05-31 | 2017-05-31 | A kind of aero-engine fuel metering system improvement strategy and its controller design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710397511.5A CN107100744B (en) | 2017-05-31 | 2017-05-31 | A kind of aero-engine fuel metering system improvement strategy and its controller design method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107100744A CN107100744A (en) | 2017-08-29 |
| CN107100744B true CN107100744B (en) | 2018-11-09 |
Family
ID=59659989
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710397511.5A Active CN107100744B (en) | 2017-05-31 | 2017-05-31 | A kind of aero-engine fuel metering system improvement strategy and its controller design method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107100744B (en) |
Families Citing this family (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107762638B (en) * | 2017-11-15 | 2019-05-24 | 中国航发南方工业有限公司 | The method and apparatus of fanjet line inspection idling rating minimum fuel flow |
| CN108087124B (en) * | 2017-12-20 | 2019-10-25 | 中国航发长春控制科技有限公司 | A kind of indirect oil-return type differential pressure valve of negative feedback control |
| CN108416086B (en) * | 2018-01-25 | 2021-07-16 | 大连理工大学 | Aero-engine model self-adaptive correction method based on deep learning |
| CN108869078A (en) * | 2018-06-26 | 2018-11-23 | 芜湖钻石航空发动机有限公司 | Aero-engine high-pressure common-rail fuel system |
| CN109506723B (en) * | 2018-11-21 | 2021-05-28 | 中国航发西安动力控制科技有限公司 | Variable-pressure-difference metering method and device |
| CN109519285B (en) * | 2018-11-21 | 2021-04-20 | 中国航发西安动力控制科技有限公司 | Aircraft engine fuel flow control system and aircraft engine |
| CN109899161B (en) * | 2019-03-07 | 2020-12-15 | 中国科学院工程热物理研究所 | Liquid fuel metering device |
| FR3094086B1 (en) * | 2019-03-19 | 2021-03-19 | Safran Aircraft Engines | Method for monitoring the operating state of a hydromechanical unit |
| CN110673663B (en) * | 2019-09-05 | 2023-03-24 | 中国航发北京航科发动机控制系统科技有限公司 | Hydraulic control system and method for testing fuel metering assembly of aircraft engine |
| CN111413866B (en) * | 2020-03-06 | 2021-08-06 | 大连理工大学 | Time delay considered aero-engine distributed control law design and verification method |
| CN111413867B (en) * | 2020-03-12 | 2021-08-10 | 大连理工大学 | Rapid modeling and optimization method for equivalent controller of hydraulic control mechanism on Flowmaster platform |
| CN111856919A (en) * | 2020-06-15 | 2020-10-30 | 西北工业大学 | Fault-tolerant controller for gain scheduling of failure of gas path component of aero-engine |
| CN111927637B (en) * | 2020-08-11 | 2023-05-23 | 中国航发北京航科发动机控制系统科技有限公司 | Fuel oil emergency oil supply mechanism and emergency oil supply method |
| CN113803179B (en) * | 2021-09-18 | 2023-03-24 | 北京航空航天大学 | Engine control method and device and electronic equipment |
| CN114046206B (en) * | 2021-11-05 | 2023-10-20 | 中国航发西安动力控制科技有限公司 | Closed-loop regulation control device for oil supply selection and switching of combined pump |
| CN114483324B (en) * | 2022-01-10 | 2023-06-09 | 江苏大学 | Fuel metering valve regulated and controlled by binary coded digital valve array and control method thereof |
| CN115454007A (en) * | 2022-09-30 | 2022-12-09 | 北京航空航天大学 | Closed-loop control system and method for constant pressure valve of fuel servo of aircraft engine |
| CN115653759B (en) * | 2022-10-13 | 2024-06-18 | 中国航发四川燃气涡轮研究院 | Afterburner oil supply system based on flow distribution and control flow design method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3530666A (en) * | 1967-01-13 | 1970-09-29 | Rolls Royce | Gas turbine engine fuel system |
| CN1563692A (en) * | 2004-04-02 | 2005-01-12 | 北京航空航天大学 | Fuel regulator of turbine jet |
| CN202228745U (en) * | 2011-07-07 | 2012-05-23 | 沈阳冠能燃气轮机科技有限公司 | Isobaric difference valve in flow regulating valve |
| CN102575585A (en) * | 2009-09-23 | 2012-07-11 | 涡轮梅坎公司 | Fuel flowmeter having an improved control device |
| WO2015009931A1 (en) * | 2013-07-19 | 2015-01-22 | Woodward, Inc. | Parallel metering pressure regulation system for a thermal efficient metering system |
| EP2891768A1 (en) * | 2014-01-06 | 2015-07-08 | Rolls-Royce Controls and Data Services Limited | Engine fuel control system |
| CN105370413A (en) * | 2014-08-25 | 2016-03-02 | 中航商用航空发动机有限责任公司 | Aircraft engine fuel oil metering system and control method thereof |
| CN205277651U (en) * | 2016-01-13 | 2016-06-01 | 中国航空动力机械研究所 | A device for servo control and engine thereof |
| CN205689340U (en) * | 2016-06-21 | 2016-11-16 | 中航商用航空发动机有限责任公司 | Aero-engine parking jettison gear, oil supply system and aero-engine |
-
2017
- 2017-05-31 CN CN201710397511.5A patent/CN107100744B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3530666A (en) * | 1967-01-13 | 1970-09-29 | Rolls Royce | Gas turbine engine fuel system |
| CN1563692A (en) * | 2004-04-02 | 2005-01-12 | 北京航空航天大学 | Fuel regulator of turbine jet |
| CN102575585A (en) * | 2009-09-23 | 2012-07-11 | 涡轮梅坎公司 | Fuel flowmeter having an improved control device |
| US9239010B2 (en) * | 2009-09-23 | 2016-01-19 | Turbomeca | Fuel flowmeter having an improved regulator device |
| CN202228745U (en) * | 2011-07-07 | 2012-05-23 | 沈阳冠能燃气轮机科技有限公司 | Isobaric difference valve in flow regulating valve |
| WO2015009931A1 (en) * | 2013-07-19 | 2015-01-22 | Woodward, Inc. | Parallel metering pressure regulation system for a thermal efficient metering system |
| EP2891768A1 (en) * | 2014-01-06 | 2015-07-08 | Rolls-Royce Controls and Data Services Limited | Engine fuel control system |
| CN105370413A (en) * | 2014-08-25 | 2016-03-02 | 中航商用航空发动机有限责任公司 | Aircraft engine fuel oil metering system and control method thereof |
| CN205277651U (en) * | 2016-01-13 | 2016-06-01 | 中国航空动力机械研究所 | A device for servo control and engine thereof |
| CN205689340U (en) * | 2016-06-21 | 2016-11-16 | 中航商用航空发动机有限责任公司 | Aero-engine parking jettison gear, oil supply system and aero-engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107100744A (en) | 2017-08-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107100744B (en) | A kind of aero-engine fuel metering system improvement strategy and its controller design method | |
| US10934944B2 (en) | Method for optimization of transient control law of aero-engine | |
| CN106774468A (en) | Flow rate controlling method | |
| WO2020186382A1 (en) | Simulink modeling method for mechanical hydraulic device of aero-engine fuel regulator | |
| CN103123504A (en) | Speed change pressure flow field control method applicable to intermittent transonic speed wind tunnel | |
| CN101887267B (en) | Mach number controller in wind tunnel | |
| CN100422451C (en) | Mechanical digger full power control system and method | |
| CN106696341B (en) | A kind of the passive type dynamic leveling control system and its control method of hydraulic press | |
| CN109783998B (en) | Simulink modeling method for mechanical hydraulic device of aero-engine fuel regulator | |
| CN106679925A (en) | High-precision control device and control method for micro-mass jet flow rate | |
| CN108180180B (en) | Double-hydraulic-cylinder flow compensation synchronous erecting device and control method thereof | |
| CN113008507A (en) | High-flow high-stability Mach number wind tunnel rapid adjusting system and method based on temporary flushing gas source | |
| CN107165892B (en) | A kind of sliding-mode control of electrohydraulic servo system | |
| CN103868670A (en) | Mach number control method of experimental section flow field of continuous transonic wind tunnel | |
| CN111352450B (en) | Digital proportional valve flow control system and method | |
| CN104772653A (en) | Liquid static pressure guide rail oil film thickness control system and method based on oil temperature compensation | |
| CN212433647U (en) | Wide-range high-precision gas pressure and flow quick adjusting device | |
| CN107975519A (en) | A kind of servo-hydraulic energy double closed-loop control system and method | |
| CN113157010A (en) | Depth variable thrust engine thrust regulation and control method and device and electronic equipment | |
| CN105775147B (en) | A kind of airplane intake closed-loop flow control device and control method | |
| CN110500330A (en) | A kind of anti-bias load adjustable speed synchronous valve, synchronous control system and working method | |
| CN212272670U (en) | Electric hydraulic control system based on two different valves parallel control hydraulic cylinders | |
| CN105436378A (en) | Low speed control system for isothermal thermal forming hydraulic machine | |
| CN103292004A (en) | High-speed forging valve control device of hydraulic forging machine | |
| CN113253606B (en) | Calibration box high-pressure air supply and vacuum air suction combined control system and method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | 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 |