CN108150295A - A kind of unmanned plane engine start control method - Google Patents
A kind of unmanned plane engine start control method Download PDFInfo
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- CN108150295A CN108150295A CN201711173415.9A CN201711173415A CN108150295A CN 108150295 A CN108150295 A CN 108150295A CN 201711173415 A CN201711173415 A CN 201711173415A CN 108150295 A CN108150295 A CN 108150295A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The present invention relates to a kind of unmanned plane engine start control methods, belong to technical field of engines.The present invention devises a kind of unmanned plane engine start control method, including unmanned plane engine ignition starting preparation stage, the control method of ignition phase, realize engine stabilizer, safe and reliable ignition start, the mechanical damage and Thermal Shock Damage of ignition start process engine structure are reduced, meets the use demand of unmanned plane engine.
Description
Technical field
The present invention relates to technical field of engines, and in particular to a kind of unmanned plane engine start control method.
Background technology
Increasingly urgent for the demand of middle-size and small-size power plant as unmanned plane market is flourished, unmanned mechanomotive force is non-
The often access times and engine operational life of concern engine.A large amount of engineering experience shows turbogenerator fast starting pair
The low cycle fatigue life of engine has a significant impact.Unmanned plane is relatively low to the starting rapidity requirement of engine, therefore nobody
Machine is to reduce starting speed while starting reliability is ensured with the design principle of turbogenerator starting stage fuel supply rate curve
Rate, slowing down product low cycle fatigue life in engine startup influences.The unmanned plane is sent out with small-sized birotary burbine fan
The basic theory of constitution of motivation is that low pressure rotor is made of level-one fan and level-one low-pressure turbine, and high pressure rotor is calmed the anger by high pressure
Machine (including level-one axial flow compressor and level-one inclined flow air compressor) and level-one high-pressure turbine composition, the form of combustion chamber is half baffling
Toroidal combustion chamber, exhaust form are vented respectively for inside and outside culvert.The outstanding feature of the engine is that size is small, light-weight, structure is tight
It gathers, working service is simple.
By engine control system analog simulation and verification experimental verification, for rotor speed in engine ignition starting process
The engine low cycle fatigue that the reasons such as quick increase, combustion chamber and the raising of turbine part temperature moment generate damages, overtemperature damage
Etc. rough sledding, formulate the control method of engine ignition starting stage, realize engine stabilizer, safe and reliable light a fire
It is dynamic, the mechanical damage and Thermal Shock Damage of ignition start process engine structure are reduced, meets making for unmanned plane engine
Use demand.
Invention content
(1) technical problems to be solved
The technical problem to be solved by the present invention is to：How a kind of unmanned plane engine start control method is designed, with reality
Existing engine stabilizer, safe and reliable ignition start.
(2) technical solution
In order to solve the above-mentioned technical problem, a kind of unmanned plane engine start control method, includes the following steps：
S1, it is controlled before ignition using following engine fuel control strategy：
Engine fuel control be power-up to receive it is fast in fuel flow proportioner between " instruction ready to start " signal
Fast solenoid-driven signal is 0, and the fast electromagnetic valve in fuel flow proportioner is in off position, when engine height is walked around fast Nh
The quick electromagnetic valve drive signal exported during design maximum (top) speed more than or equal to 10% is still 0, quick in fuel flow proportioner
Solenoid valve is still within off position, and the engine height fast Nh that walks around is strong within 10% design maximum (top) speed more than a period of time
Quick electromagnetic valve drive signal 0 processed, the engine height fast Nh that walks around judge after 10% design maximum (top) speed more than a period of time
Oil-pin position：If fuel oil actual value is higher than 83.3% maximum fuel value, quick electromagnetic valve drive signal is set, makes fuel oil spindle
Engine ignition actual needs position is returned to prestissimo, into normal control；The design maximum (top) speed is high for engine
Press rotor speed maximum value；
S2, it is controlled in ignition process using gradual starting control strategy：
Engine carries out combustion chamber ignition in igniting according to initial ignition fuel flow, judges combustion chamber ignition success
Afterwards, increase fuel supply volume according to the scheduled fuel flow rate of rise, be carried out at the same time the judgement of engine start success conditions, when
Satisfaction is started using igniting fueling strategy is exited after successfully criterion, otherwise up to engine startup maximum igniting fuel flow
Preferably, the initial ignition fuel flow determines as follows：According to engine chamber characteristics of components,
For initial ignition fuel flow described in different ignition altitudes, different igniting Design of Rotation.
Preferably, the maximum igniting fuel flow determines as follows：It is set as the oil mass than minimum steady state condition
It is higher by more than 30%.
Preferably, the igniting fueling strategy that exits is：Engine increases in combustion chamber ignition success, and according to default fuel feeding
Dosage carries out gradual starting control strategy, speed control strategy and oil-gas ratio control plan during idling rating climbs
Comparison slightly works by the condition selection thrin of fuel oil minimum supply.
Preferably, described a period of time is 4 seconds.
(3) advantageous effect
The present invention devises a kind of unmanned plane engine start control method, is started including unmanned plane with engine ignition
Preparation stage, the control method of ignition phase realize engine stabilizer, safe and reliable ignition start, reduce and light a fire
The mechanical damage and Thermal Shock Damage of dynamic process engine structure meet the use demand of unmanned plane engine.
Description of the drawings
Fig. 1 is that the fuel flow in engine ignition stage controls to adjust method schematic diagram；
Fig. 2 is the logic choice relation figure of engine control strategy；
Fig. 3 is twin shaft mixed exhaust turbofan model structure, schematic cross-section；
Fig. 4 is engine control system model value analogous diagram；
Fig. 5 is gradual fueling strategy control law curve graph；
Fig. 6 is the calculating of igniting front engine fuel flow and adjusting method test effect curve graph；
Fig. 7 is engine start-up phase trial curve figure after phase III software optimization；
Fig. 8 is ignition phase engine fuel flow control policy method test effect curve figure.
Specific embodiment
To make the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to the present invention's
Specific embodiment is described in further detail.
A large amount of engineering experience and theoretical analysis shows that, rotor speed quickly increases, fires in engine ignition starting process
Phenomena such as temperature moment of burning room and turbine part raising, may cause engine low-cycle fatigue damage, Thermal Fatigue Damage etc. occur
Rough sledding.With reference to the starting control strategy of domestic and international advanced engine, pass through engine control system analog simulation and experiment
Verification, formulates the control strategy method in rational engine start preparation stage, ignition start stage, reduces ignition start mistake
The fatigue stress and thermal shock effect that engine rotating structural elements, high-temperature component are subject in journey, realize engine stabilizer, safety,
Reliable ignition start meets the use demand of unmanned plane engine.
It after engine is installed on the aircraft such as unmanned plane, needs to carry out multiple ignition start, since engine ignition rises
High pressure rotor rotating speed quickly climbs during dynamic, and combustion chamber, high-pressure turbine temperature sharply increase, engine high pressure turbine rotor portion
Part is relatively also easy to produce ablation, Thermal Shock Damage caused by low all cyclic fatigues and overtemperature, it will reduces the service life of engine.
The present invention has formulated a kind of stabilization, the safe and reliable unmanned plane engine start preparation stage, has lighted a fire thus
The fuel injection control strategy method in dynamic stage, this method include igniting front engine fuel injection control strategy, the combustion of ignition phase engine
Oily control strategy.
1. front engine fuel injection control strategy of lighting a fire
In traditional design concept, in order to protect the fast electromagnetic valve in engine oil adjuster, it is desirable that controlled in number
Device processed arrives the fast electromagnetic valve driving between " instruction ready to start " signal for receiving aircraft in fuel flow proportioner after the power is turned on
Signal 0, that is, fast electromagnetic valve is made to be in off position；When digitial controller receive " instruction ready to start " signal and
When height walks around fast Nh more than or equal to 10% design maximum (top) speed, the control operation of engine fuel is proceeded by.Due to unmanned plane
Ignition start is carried out after blowing forwarding motivation to certain rotating speed using ground high-pressure air source, the mistake of high pressure air-blowing forwarding motivation on ground
Cheng Zhong, according to traditional Preservation tactics, quick electromagnetic valve drive signal is 0, and the fast electromagnetic valve in fuel flow proportioner does not work
When, due to lacking driving, engine fuel position will increase with engine speed and be moved to maximum position, when rotating speed exceeds
After 10% design maximum (top) speed, engine control system participates in controlling according to default control rule, quick in fuel flow proportioner
Solenoid valve is started to work, and engine fuel position is moved according to actual demand to target location, since control operation uses the time
The mode of integration, oil-pin position returns to target location by maximum position needs the long period.When digitial controller receives " starting point
During fire instruction ", engine fuel position is larger, and the fuel flow of supply engine combustion chamber causes far above actual needs value
Fuel-rich combustion in engine ignition starting stage combustion chamber generates larger temperature to engine chamber and high-temperature component and rushes
It hits, limiting case will cause engine thermal component ablation occur.
The present invention has formulated following technical solution regarding to the issue above by control strategy analog simulation and verification experimental verification：
It is 0 that digitial controller, which is power-up to and receives quick electromagnetic valve drive signal between " instruction ready to start " signal, fuel flow proportioner
In fast electromagnetic valve be in off position, when height walk around fast Nh more than or equal to 10% design maximum (top) speed when export it is quick
Solenoid-driven signal is still 0, and the fast electromagnetic valve in fuel flow proportioner is still within off position.Engine height is walked around speed
Nh forces quick electromagnetic valve drive signal 0 in 10% design maximum (top) speed more than 4s, and height walks around fast Nh in 10% design maximum
Judge oil-pin position after rotating speed more than 4s：If fuel oil actual value is higher than 83.3% maximum fuel value, setting fast electromagnetic valve drives
Signal 100 makes spindle be quickly returning to engine ignition actual needs position, into normal control.The strategy can not only ensure
Engine igniting time fuel oil can also before ignition check the flexibility of engine spindle, work as oil in suitable position
When bite occurs in needle, termination process and alarm perform effectively, the execution of the strategy for the strategy before ensureing engine ignition
Condition of the feedback as engine " allowing to light a fire ", feeds back to aircraft computer, starts function as aircraft interpretation
The foundation of no ignition start.
2. engine fuel control strategy in ignition process
The more general starting ignition fuel supply rate curve of aero-engine is Wf/P3=f (Nh) at present, and Wf, P3 are combustion respectively
Burn indoor fuel flow and air stream, reflection is burnt indoor oil gas ratio characteristic, and Nh walks around fast Nh for engine height.Such control
Oil-gas ratio range of the strategy according to engine chamber steady operation can reflect the physical characteristic of burning, still better
Fuel system compares the consistency and measuring accuracy dependent on fuel-flow control, in engine control system fuel-flow control and metering essence
When degree cannot be met the requirements, Amount of actual oil supply meeting off-design requirement, while the strategy is using engine combustion chamber pressure as combustion
, for small turbine engine, easily there is chamber pressure in ignition point and quickly increases in the calculating parameter of oil supply, so as to phase
Fuel delivery is answered to sharply increase, causes engine ignition priming speed very fast, rotor-support-foundation system relative speed variation, combustion chamber and turbine
Part temperatures sharply increase, and it is unfavorable that engine is used for multiple times.
The starting control strategy of the present invention carries out the combustion chamber stable operation characteristics of unmanned plane small turbine engine
Statistics, can be to burn according to engine chamber after the success of the oil-gas ratio parameter and engine ignition of stable ignition during small operating mode
The oil-gas ratio parameter of room formulates a kind of gradual fueling strategy being suitable for small turbine engine ignition start.Engine exists
Combustion chamber ignition is carried out according to initial ignition fuel flow during igniting, after judging combustion chamber ignition success, according to scheduled fuel oil
The rate of rise increases fuel supply volume, is carried out at the same time the judgement of engine start success conditions, and successfully criterion retrogressing is started when meeting
Go out fueling strategy of lighting a fire, otherwise until maximum fuel flow restriction, this method can farthest reduce fanjet and rise
The damage to engine structure such as low-cycle fatigue, temperature shock in dynamic improves the service life of engine.The strategy mainly wraps
It includes initial ignition oil mass to determine, the limitation of maximum point kerosene amount determines, the oil mass rate of rise of lighting a fire and exits starting ignition control
The parts such as rule condition.
1) initial ignition fuel flow determines
For turbine engine combustion chamber under conditions of import stagnation pressure, total temperature are certain, various inlet flow corresponds to certain
The oil-poor of condition, rich oil igniting oil mass boundary can ensure the reliable ignition of combustion chamber in bounds.It is fired according to engine
Room characteristics of components is burnt, the initial fuel for formulating combustion chamber reliable ignition for different ignition altitudes, different high pressure rotor rotating speeds supplies
To amount, while electric ignition device and engine start oil circuit work schedule and working time are designed, so that engine chamber can
With stabilization, reliable ignition success, and pass through ground, high-altitude ignition verification experimental verification.
2) maximum point kerosene amount limitation determines
Since minimum working condition, engine minimum operating mode when control law switches will be transferred to after engine ignition success
Related with temperature of incoming flow, if temperature is relatively low, the physics rotating speed of minimum operating mode can reduce, and then required fuel flow can reduce；
If temperature is higher, the physics rotating speed raising of minimum operating mode, required fuel flow can increase, required if temperature further increases
For fuel flow once being more than the maximum fuel flow restriction value of gradual starting control dypass, then will appear can not be transferred to stable state control
The situation of rule processed.Therefore the maximum oil mass of gradual starting control need to be higher by more than 30% than the oil mass of minimum steady state condition,
To ensure to switch successfully.
3) the igniting oil mass rate of rise
Fast Nh ascending amounts are walked around by height or chamber temperature value added judges the success of engine chamber stable ignition
Afterwards, start the fuel supply volume according to certain slope increase combustion chamber, ensure during fuel flow increase, engine is not
There is transient state excess revolutions and overtemperature and combustion chamber, fan, compressor unstable operation, according to engine high-temperature rotary part
Material property controls the climbing speed of engine speed and chamber temperature.The setting of the fuel oil incrementss is the pass of the present invention
Bond parameter.By Control system simulation emulation and verification experimental verification, the type turbine engine combustion chamber is formulated and has lighted a fire successfully and climb
Being raised to the fuel oil of small operating mode steady operation increases magnitude.
4) starting ignition control law condition is exited
Engine during idling rating climbs, is sent out in combustion chamber ignition success, and to according to default fuel feeding incrementss
The comparison of gradual starting control strategy, speed control strategy and oil-gas ratio control strategy is carried out inside motivation controller, is pressed
The condition selection thrin of fuel oil minimum supply works.The choice relation of engine control strategy as shown in Figure 2, until
Engine exits ignition control rule, into stable state control law.
It is two shaft turbofan mixing without boost engine that the present invention, which implements the engine that is related to, containing fan, axial flow compressor, tiltedly
The components such as flow air compressor, combustion chamber, high-pressure turbine, low-pressure turbine, provided with internal duct and external duct jet pipe.In order to carry out engine control system
Design and verification experimental verification work, establish engine mockup according to each characteristics of components data of engine, model structure and section are determined
Justice as shown in figure 3, engine be equipped with 5 sensor monitorings, control engine behavior, including rotational speed of lower pressure turbine rotor Nl,
Total temperature after stagnation pressure Pt3 and high-pressure turbine after air flow temperature sensor Tt22, high-pressure compressor after high pressure rotor rotating speed Nh, fan
Tt5。
The control system of the h type engine h is made of controller unit, engine sensor, fuel oil adjustment actuating mechanism,
Middle controller unit is the core equipment of engine control system, and function is to perform the engine phase that aircraft computer is sent
Instruction is closed, and combines the acquisition signal of the various sensors of engine, control fortune is carried out according to the control algolithm in controller unit
It calculates, provides drive signal, the throttle of fuel regulator is controlled move, so that change burning room fuel delivery size is to realize engine
The control of working condition.Fig. 4 is the basic principle figure of engine control system.
To Mr. Yu's small sized turbine Duct-Burning Turbofan, ignition phase fuel flow control method is：
Aircraft sends out preset fixed throttle qmf_start after starting order, carries out engine chamber igniting, works as high pressure
Rotor speed Nh increases super than the starting order moment more than total temperature Tt5 after 3000r/min or high-pressure turbine than the starting order moment
When crossing 50 DEG C, fuel feed is stepped up according to the time, the maximum fuel feeding of the rule is limited to qmf_end.Oil mass of lighting a fire rises
Slope rate is 2.5kg/s, as shown in Figure 5.
Qmf_start=50 × PH/101.325, qmf_end unit are kg/h；
Qmf_end=120 × PH/101.325；
PH=101.325 × (1-H/44.308) 5.2553 × 103, PH units are kPa；H is high for engine work in formula
Degree, unit km.
Igniting preparation stage engine fuel control strategy applicating example：
In traditional design concept, in order to protect the fast electromagnetic valve in engine oil adjuster, it is desirable that controlled in number
Device processed arrives the fast electromagnetic valve driving between " instruction ready to start " signal for receiving aircraft in fuel flow proportioner after the power is turned on
Signal 0, that is, fast electromagnetic valve is made to be in off position；When digitial controller receive " instruction ready to start " signal and
When height walks around fast Nh more than or equal to 10% design maximum (top) speed, the control operation of engine fuel is proceeded by.Due to unmanned plane
Ignition start is carried out after blowing forwarding motivation to certain rotating speed using ground high-pressure air source, the mistake of high pressure air-blowing forwarding motivation on ground
Cheng Zhong, according to traditional Preservation tactics, quick electromagnetic valve drive signal is 0, and the fast electromagnetic valve in fuel flow proportioner does not work
When, due to lacking driving, engine fuel position will increase with engine speed, and maximum position movement is reached in the about 2s times,
After rotating speed is beyond 10% design maximum (top) speed, engine control system participates in controlling according to default control rule, fuel control
Fast electromagnetic valve in device is started to work, and engine fuel position is moved according to actual demand to target location, since control is transported
It calculates by the way of time integral, oil-pin position returns to target location by maximum position needs the long period.The about 13s times can be with
Target location is reached, if sending out starting order in 13s, since engine fuel open position is larger when digitial controller is received
To when " starting ignition instruction ", the fuel flow of supply engine combustion chamber leads to engine ignition far above actual needs value
Fuel-rich combustion in starting stage combustion chamber generates larger temperature shock, limiting case to engine chamber and high-temperature component
Engine thermal component will be caused ablation occur.
The perfect of engine ignition preparation stage fuel injection control strategy has been carried out thus：Digitial controller, which is power-up to, to be received
Quick electromagnetic valve drive signal is 0 between " instruction ready to start " signal, and the fast electromagnetic valve in fuel flow proportioner is in not work
Make state, the quick electromagnetic valve drive signal exported when height walks around fast Nh more than or equal to 10% design maximum (top) speed is still 0, is supplied
Fast electromagnetic valve in oil conditioner is still within off position.Engine height walk around fast Nh 10% design maximum (top) speed with
Quick electromagnetic valve drive signal 0 is forced in upper 4s, height, which is walked around after fast Nh designs maximum (top) speed more than 4s 10%, judges spindle position
It puts：If fuel oil actual value is higher than 83.3% maximum fuel value, setting quick electromagnetic valve drive signal 100 is quickly returning to spindle
Position is actually needed in engine ignition, into normal control.The strategy can not only ensure that engine igniting time fuel oil is closing
Right position is put, and the flexibility of engine spindle can also be checked before ignition, and when bite occurs in spindle, termination process is simultaneously
Alarm is performed effectively for the strategy before ensureing engine ignition, and the execution feedback of the strategy " allows as engine
Igniting " condition, feed back to aircraft computer, as aircraft interpretation engine can ignition start foundation.
Fig. 6 is taking the design strategy to take engine start situation comparison diagram after the design method by curve is visible
After method, engine can adjust the wind for target ignition oil level, reducing rich down-firing in time before starting order
Danger.
Ignition start stage engine fuel control strategy applicating example：
To reduce ignition start process engine rotating structural elements, the fatigue stress that high-temperature component is subject to and temperature shock shadow
It rings, takes the trial curve after starting stage engine fuel control strategy method of lighting a fire in the present invention as shown in Figure 7.It lights a fire
Gradual fuel injection control strategy of dynamic stage and traditional bullet are compared as shown in Figure 8 with oil-gas ratio control strategy.As shown in Figure 8, start
Machine under conditions of the fixation throttle 50kg/h of fuel regulator combustion chamber rapid-ignition success, until engine height is walked around fast Nh compared with
After " starting order " moment grows beyond 3000r/min, increase fuel delivery according to fixed slope, engine independently climbs, the phase
Between engine control logic judge, wherein a certain control law is selected to work, by starting control strategy after the 18.3s times
Smoothly it is cut into engine minimum working condition.
By comparing ignition start stage gradual fuel injection control strategy and traditional oil-gas ratio control strategy, height is walked around fast Nh
During for 40% design maximum (top) speed, under gradual control strategy, the fuel flow of engine start-up phase is than traditional oil-gas ratio
The fuel flow of fueling strategy supply engine combustion chamber reduces by 30%.Starting process engine speed change rate is no more than
1000r/min/s, starting process is soft, can effectively reduce fatigue damage and thermal stress in engine startup, carry
The service life of high engine.
The present invention prepares rank for unmanned plane turbogenerator ground start technical field by formulating engine ignition
Section, ignition phase engine fuel control strategy, reduce ignition start process engine rotating structural elements, high-temperature component by
The fatigue stress and temperature shock arrived influences.The invention is on the basis of the standards and norms of aero-engine, with reference to 31
Institute's turbogenerator R＆D experience for many years, passes through the emulation of a large amount of Control system simulation and overall test is studied, and realizes turbine
Engine stabilizer, safe and reliable ignition start are simultaneously switched to minimum steady-working state, meet unmanned plane engine
Multiple igniting, the use demand of long-life.The invention is applied in a variety of unmanned planes on turbogenerator, and have passed through
Ignition start experiment examination after block testing stand and engine installation, result of the test show using this fuel injection control strategy
Design method, meet multiple igniting, the use demand of long-life of unmanned plane engine.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvement and deformation can also be made, these are improved and deformation
Also it should be regarded as protection scope of the present invention.
Claims (5)
1. a kind of unmanned plane engine start control method, which is characterized in that include the following steps：
S1, it is controlled before ignition using following engine fuel control strategy：
Engine fuel control is power-up to the fast electric received between " instruction ready to start " signal in fuel flow proportioner
Magnet valve drive signal is 0, and the fast electromagnetic valve in fuel flow proportioner is in off position, when the engine height fast Nh that walks around is more than
The quick electromagnetic valve drive signal exported during design maximum (top) speed equal to 10% is still 0, the quick electromagnetic in fuel flow proportioner
Valve is still within off position, and engine height is walked around, and pressure is fast in a period of time more than 10% design maximum (top) speed by fast Nh
Fast solenoid-driven signal 0, the engine height fast Nh that walks around judge spindle after 10% design maximum (top) speed more than a period of time
Position：If fuel oil actual value is higher than 83.3% maximum fuel value, quick electromagnetic valve drive signal is set, makes fuel oil spindle with most
Fast speed returns to engine ignition actual needs position, into normal control；The design maximum (top) speed turns for engine high pressure
Rotor speed maximum value；
S2, it is controlled in ignition process using gradual starting control strategy：
Engine carries out combustion chamber ignition in igniting according to initial ignition fuel flow, after judging combustion chamber ignition success, presses
Increase fuel supply volume according to the scheduled fuel flow rate of rise, be carried out at the same time the judgement of engine start success conditions, work as satisfaction
It starts using igniting fueling strategy is exited after successfully criterion, otherwise the fuel flow until engine startup maximum is lighted a fire.
2. the method as described in claim 1, which is characterized in that the initial ignition fuel flow determines as follows：
According to engine chamber characteristics of components, for initial ignition fuel oil stream described in different ignition altitudes, different igniting Design of Rotation
Amount.
3. the method as described in claim 1, which is characterized in that the maximum igniting fuel flow determines as follows：
It is set as being higher by more than 30% than the oil mass of minimum steady state condition.
4. the method as described in claim 1, which is characterized in that it is described exit igniting fueling strategy be：Engine is in combustion chamber
It lights a fire successfully, and according to default fuel feeding incrementss during idling rating climbs, carries out gradual starting control strategy, rotating speed
The comparison of control strategy and oil-gas ratio control strategy works by the condition selection thrin of fuel oil minimum supply.
5. method according to any one of claims 1 to 4, which is characterized in that described a period of time is 4 seconds.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110578609A (en) * | 2019-09-23 | 2019-12-17 | 辽宁壮龙无人机科技有限公司 | method and device for regulating and controlling engine ignition and readable storage medium |
| CN112413645A (en) * | 2020-11-19 | 2021-02-26 | 中国航发沈阳发动机研究所 | Method and system for boosting ignition oil supply of aircraft engine |
| CN112483259A (en) * | 2020-11-04 | 2021-03-12 | 北京动力机械研究所 | Turbofan engine precombustion chamber ignition starting method changing along with height |
| CN114109616A (en) * | 2021-11-05 | 2022-03-01 | 江西洪都航空工业集团有限责任公司 | Engine high-altitude starting oil supply adjusting method, device and system |
| CN114458400A (en) * | 2021-12-18 | 2022-05-10 | 北京动力机械研究所 | Open-loop turbine engine steady-state control method |
| CN114893301A (en) * | 2022-04-14 | 2022-08-12 | 北京动力机械研究所 | Small turbofan engine parameter fault judgment method and redundancy control method |
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