CN106321252B - The starting process fuel oil control method and system of a kind of aero-engine - Google Patents
The starting process fuel oil control method and system of a kind of aero-engine Download PDFInfo
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- CN106321252B CN106321252B CN201510342178.9A CN201510342178A CN106321252B CN 106321252 B CN106321252 B CN 106321252B CN 201510342178 A CN201510342178 A CN 201510342178A CN 106321252 B CN106321252 B CN 106321252B
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Abstract
The invention discloses the starting process fuel oil control method and system of a kind of aero-engine.Surge margin limitation protection is carried out according to the surge margin desired value of setting and the surge margin value of calculating to calculate, and obtains surge margin output valve, and according to the corresponding relation of surge margin output valve and temperature adjustmemt amount, obtain temperature adjustmemt amount；Temperature protection calculating is carried out according to the temperature margin desired value of setting, the engine temperature value obtained and temperature adjustmemt amount, obtains temperature value output, according to temperature value output and the corresponding relation of fuel flow value, obtains the fuel flow value at current time；Fuel flow output valve between fuel flow higher limit and lower limit is obtained according to fuel flow value, to carry out fuel feeding to engine according to the fuel flow output valve.The present invention avoids examination manually from gathering to obtain N2The tedious work of dot control plans.
Description
Technical field
The invention belongs to the starting process fuel oil control method of aero-engine control, more particularly to a kind of aero-engine
And system.
Background technology
The normal starting process of aero-engine (gas-turbine unit) is divided into three ranks with the rise of rotating speed
Section：1) individually band forwards motivation to starter；2) engine is lighted a fire after reaching certain rotating speed, engine oil, starter and turbine
Common band forwarding motivation；3) starter disengages, and individually band forwards motivation to idling rating to turbine.Wherein start the control of fuel oil
Journey is related to above-mentioned the 2nd and the 3rd stage.
Traditional Aero-Engine Start process fuel oil control method is that (starting control refers to aero-engine for oil-gas ratio control
The changing rule to control input during idling rating is started from dead ship condition).Oil-gas ratio control be it is a kind of by amount of fuel and
The ratio of compressor delivery pressure come realize transition state control opened loop control plan, do not possess vulnerability to jamming, in broad range
Need to be modified plan during use.
Based on compressor rotor acceleration (N2Dot starting process fuel oil control method) is of great interest (to be added
Speed control refers to aero-engine during transition state, by adjusting engine fuel flow, obtains desired engine and turns
The rate of change of rotor speed), this method can make the engine of all same models all have identical starting performance, even if to each other
In the presence of difference caused by manufacture and material error；And after engine performance is degenerated, starting performance is maintained to constant.
As based on oil-gas ratio control, the starting control based on rotor acceleration is also required to formulate corresponding reference in advance
Control plan, these plans are usually to be dispatched by rotor speed.How to obtain such control plan is that a key is asked
Topic.The factor that the starting process of High Performance Aeroengine mainly considers be meet certain surge margin, blowoff limit and
Turbine inlet temperature nargin, and the starting time is reduced as far as possible in the case where meeting above-mentioned condition.Traditional starting process design method,
It is by engine performance simulation model, designs N2Dot control plans, then test run, constantly debugging are started by engine, repair
Change control plan, to reach all restrictive condition requirements, such implementation method does not have the function of Automatic Optimal, and can cause
It is larger to retain nargin, it is impossible to give full play to engine performance.
Meanwhile from N2The angle that dot controls are realized is, it is necessary to design N2Dot controllers.N2Dot control loops have itself
Feature, its controlled device have a pure differential link, therefore 90 degree of phase angle is brought from the perspective of frequency analysis
In advance, so that N2Dot control loops have a very high stability margin, but the classical for example interior mould parameter of Frequency Design method
Change method, loop forming method can not be directed to the controlled device design controller with pure differential link.
The content of the invention
The technical problem to be solved in the present invention be meet during Aero-Engine Start surge margin, blowoff limit with
And under conditions of temperature margin, obtain N in starting process2Dot control plans, avoid examination manually and gather to obtain this plan
Tedious work.
According to an aspect of the present invention, a kind of starting process fuel oil control method of aero-engine is proposed, including：
Surge margin limitation protection is carried out according to the surge margin desired value of setting and the surge margin value of calculating to calculate,
Surge margin output valve is obtained, and according to the corresponding relation of surge margin output valve and temperature adjustmemt amount, obtains temperature adjustmemt amount；
Temperature protection is carried out according to the temperature margin desired value of setting, the engine temperature value obtained and temperature adjustmemt amount
Calculate, obtain temperature value output, according to temperature value output and the corresponding relation of fuel flow value, obtain the fuel oil stream at current time
Value；
Fuel flow output valve between fuel flow higher limit and lower limit is obtained according to fuel flow value, with basis
The fuel flow output valve carries out fuel feeding to engine.
Further, in addition to：Obtain the rotating speed acceleration (N of engine2Dot) desired value, by N2Dot desired values and N2dot
Difference between calculated value inputs as controller, is calculated, is exported as rotating speed (N by differential evolution2), the differential evolution meter
Calculate to meet N2Dot is instructed and N2Dot follows the difference of signal, N2The phase margin of dot control loop open-loop transfer functions, with
And N2The cut-off frequency of dot control loop open-loop transfer functions is target, and calculating meets the control corresponding to the target
Device parameter.
Further, the up-and-down boundary value of the temperature adjustmemt amount is limited, and exports the temperature adjustmemt amount less than or equal to 0.
Further, differential evolution calculates and controller parameter is optimized, and its optimization aim is：
Wherein, e (t) is N2Dot is instructed and N2Dot follows the difference of signal, PM N2Letter is transmitted in the open loop of dot control loops
Several phase margins, Wc N2The cut-off frequency of dot control loop open-loop transfer functions, begin are initial times, and end is knot
Beam time, a, b, c are the weights of three indexs respectively；
Calculated by successive ignition, the N that last time calculates2Dot controller parameters cause desired value J to reach minimum, really
Fixed final N2Dot controller parameters.
Further, temperature sensor or engine exhaust temperature sensor obtain engine temperature value before high-pressure turbine.
Further, combustion chamber is obtained from high-pressure compressor outlet flow sensor or high-pressure compressor inlet flow rate sensor
Air flow value, according to fuel flow value and the ratio relation of air flow value, obtain fuel flow value.
Further, oil-gas ratio is obtained according to the ratio calculation of fuel flow output valve and compressor delivery pressure.
According to an aspect of the present invention, a kind of starting process fuel control system of aero-engine is proposed, including：
The surge margin limitation protective loop is used for abundant according to the surge margin desired value of setting and the surge of calculating
Angle value carries out surge margin limitation protection and calculated, and obtains surge margin output valve, and repaiied with temperature according to surge margin output valve
The corresponding relation of positive quantity, obtain temperature adjustmemt amount；
The temperature margin limitation protective loop is used for the temperature margin desired value according to setting, the engine temperature obtained
Value and temperature adjustmemt amount carry out temperature protection calculating, obtain temperature value output, according to temperature value output and fuel flow value
Corresponding relation, obtain the fuel flow value at current time；
The flame-out limitation protective loop be used for according to fuel flow value obtain fuel flow higher limit and lower limit it
Between fuel flow output valve, with according to the fuel flow output valve to engine carry out fuel feeding.
Further, in addition to：Controller, for obtaining the rotating speed acceleration (N of engine2Dot) desired value, by N2Dot mesh
Scale value and N2Difference between dot calculated values inputs as controller, is calculated, is exported as rotating speed (N by differential evolution2), it is described
Differential evolution is calculated to meet N2Dot is instructed and N2Dot follows the difference of signal, N2The phase of dot control loop open-loop transfer functions
Position nargin and N2The cut-off frequency of dot control loop open-loop transfer functions is target, and calculates and meet that the target institute is right
The controller parameter answered.
Further, the surge margin limitation protective loop limits the up-and-down boundary value of the temperature adjustmemt amount, and defeated
Go out to be less than or equal to 0 temperature adjustmemt amount.
Further, the controller performs differential evolution calculating and controller parameter is optimized, and its optimization aim is：
Wherein, e (t) is N2Dot is instructed and N2Dot follows the difference of signal, PM N2Letter is transmitted in the open loop of dot control loops
Several phase margins, Wc N2The cut-off frequency of dot control loop open-loop transfer functions, begin are initial times, and end is knot
Beam time, a, b, c are the weights of three indexs respectively；
Calculated by successive ignition, the N that last time calculates2Dot controller parameters cause desired value J to reach minimum, really
Fixed final N2Dot controller parameters.
Further, the temperature margin limits protective loop from T4Sensor or engine exhaust temperature EGT sensors obtain
Take engine temperature value.
Further, the flame-out protective loop that limits is from Wa3 sensors or high-pressure compressor inlet flow rate Wa25 sensors
The air flow value of combustion chamber is obtained, according to fuel flow value and the ratio relation of air flow value, obtains fuel flow value.
Further, the controller obtains according to fuel flow output valve and compressor delivery pressure Ps3 ratio calculation
Oil-gas ratio.
In the present invention, protected as target, directly obtained full with the limitation of surge margin, temperature margin and blowoff limit
The fuel flow output valve of the above-mentioned target of foot, and fuel feeding is carried out to engine according to the fuel flow output valve.It is thus possible to
Engine speed is obtained, and obtains N2dot control plans in starting process, examination manually is avoided and gathers to obtain the numerous of this plan
Trivial work.
By referring to the drawings to the present invention exemplary embodiment detailed description, further feature of the invention and its
Advantage will be made apparent from.
Brief description of the drawings
The accompanying drawing of a part for constitution instruction describes embodiments of the invention, and is used to solve together with the description
Release the principle of the present invention.
Referring to the drawings, according to following detailed description, the present invention can be more clearly understood, wherein：
Fig. 1 show typical gas-turbine unit.
Fig. 2 show the structural representation of the starting process fuel control system of aero-engine.
Fig. 3 show the structural representation of another embodiment of the starting process fuel control system of aero-engine.
Fig. 4 show the structural representation of another embodiment of the starting process fuel control system of aero-engine.
Fig. 5 is a kind of schematic flow sheet of the starting process fuel oil control method of aero-engine.
Embodiment
The various exemplary embodiments of the present invention are described in detail now with reference to accompanying drawing.It should be noted that：Unless have in addition
Body illustrates that the unlimited system of part and the positioned opposite of step, numerical expression and the numerical value otherwise illustrated in these embodiments is originally
The scope of invention.
Simultaneously, it should be appreciated that for the ease of description, the size of the various pieces shown in accompanying drawing is not according to reality
Proportionate relationship draw.
The description only actually at least one exemplary embodiment is illustrative to be never used as to the present invention below
And its application or any restrictions that use.
It may be not discussed in detail for technology, method and apparatus known to person of ordinary skill in the relevant, but suitable
In the case of, the technology, method and apparatus should be considered as authorizing part for specification.
In shown here and discussion all examples, any occurrence should be construed as merely exemplary, without
It is as limitation.Therefore, the other examples of exemplary embodiment can have different values.
It should be noted that：Similar label and letter represents similar terms in following accompanying drawing, therefore, once a certain Xiang Yi
It is defined, then it need not be further discussed in subsequent accompanying drawing in individual accompanying drawing.
For the object, technical solutions and advantages of the present invention are more clearly understood, below in conjunction with specific embodiment, and reference
Accompanying drawing, the present invention is described in more detail.
Fig. 1 show typical gas-turbine unit.It presses air-flow axial flow direction a, successively with low-pressure stage (wind
Fan 1 and booster stage 2)；High-pressure compressor 3, to compress the air stream into core-engine；Combustion chamber 4, fuel oil and compressed air
Mixture burnt in the combustion chamber, to produce propulsion air-flow；High-pressure turbine 5 and low-pressure turbine 6, they are turned by propulsion air-flow
It is dynamic, respectively by high-pressure shaft 8 and low-pressure shaft 9, drive high-pressure compressor and fan forced level；Jet pipe 7, turbine outlet air-flow warp
Jet pipe sprays at a high speed.
Fig. 2 show the structural representation of the starting process fuel control system of aero-engine.The system includes：Surge
Nargin limitation protective loop 21, temperature margin limitation protective loop 22 and flame-out limitation protective loop 23.Wherein：
The surge margin limitation protective loop 21 is used for according to the surge margin desired value of setting and the surge of calculating
Margin value carries out surge margin limitation protection and calculated, and obtains surge margin output valve, and according to surge margin output valve and temperature
The corresponding relation of correction, obtain temperature adjustmemt amount.In another embodiment, the surge margin limitation protective loop further defines
The up-and-down boundary value of the temperature adjustmemt amount, and export the temperature adjustmemt amount less than or equal to 0.
Wherein, it is according to P that can calculate one of surge margin value, SMhpc on-time model examples according to SMhpc on-time models3/
P25Pressure ratio is calculated, according to N2And T3Calculate engine flow value.Three rotating speed, pressure ratio and flow parameters are inputted to airborne and started
Machine performance data figure, the position of present engine operating point is calculated, the relative value of the point and engine stall margin, as sent out
The surge margin value of motivation.Here P3For high-pressure compressor outlet pressure, P25For high-pressure compressor inlet pressure, T3For high pressure pressure
Mechanism of qi outlet temperature, N2For rotating speed.
Surge margin desired value can limit protective loop 21 by the surge margin and be configured or other
Loop or unit are configured, and when needed, are obtained by surge margin limitation protective loop 21.
Surge margin limitation protective loop 21 enters according to the surge margin desired value of setting and the surge margin value of calculating
The limitation protection of row surge margin calculates, and surge margin conducted herein limitation protection calculates e.g. PID and calculated, so as to calculate
Surge margin value follow the surge margin desired value of setting, i.e. so that the surge margin value calculated and the surge margin set
Difference between desired value is as far as possible small.Certainly, surge margin limitation protection calculating is not limited to PID calculating.People in the art
Member is it is to be understood that be merely just used for for example, should not be construed as the limit value to the present invention.
It is computed, obtains surge margin output valve, the changing value of surge margin output valve and the changing value of temperature adjustmemt amount
Between there is corresponding relation, for example, linear relationship, certainly, be merely just used to illustrate, should not be construed as the limit to the present invention
Value.Surge margin output is worth to according to the output of the surge margin of the surge margin output valve at current time and previous moment
The changing value of value, and then the changing value of corresponding temperature adjustmemt amount is known that, and according to previous moment temperature adjustmemt value, meter
Calculation obtains the temperature adjustmemt amount at current time.Wherein, the temperature adjustmemt amount is also carried out to the restriction of up-and-down boundary value, and exported
Temperature adjustmemt amount less than or equal to 0 limits protective loop 22 to temperature margin.Because temperature is higher, surge margin is smaller, in order to
Allow surge margin to increase, then to reduce temperature value, then temperature adjustmemt amount of the output less than 0；If surge margin meets the requirements,
Temperature need not be adjusted, then temperature adjustmemt amount is 0.Therefore, the value of the temperature adjustmemt amount of output is less than or equal to 0.
The temperature margin limitation protective loop 22 is used for the temperature margin desired value according to setting, the engine temperature obtained
Angle value and temperature adjustmemt amount carry out temperature protection calculating, obtain temperature value output, according to temperature value output and fuel flow
Corresponding relation, obtain the fuel flow value at current time.
Temperature margin desired value can limit protective loop 22 by temperature margin and be configured or in other loops
Or unit is configured, when needed, obtained by temperature margin limitation protective loop 22.
Temperature margin limitation protective loop 22 can before high-pressure turbine temperature T4Sensor or engine exhaust temperature
Spend EGT sensors and obtain engine temperature value.
Temperature protection is carried out according to the temperature margin desired value of setting, the engine temperature value obtained and temperature adjustmemt amount
Calculate, surge margin conducted herein limitation protection calculates e.g. PID and calculated, so that the temperature value output calculated is followed and set
The temperature margin desired value put, or follow the temperature value determined by temperature margin desired value and temperature adjustmemt amount.I.e. so that
Difference between the temperature value output of calculating and the temperature margin desired value of setting is as far as possible small, or, by temperature margin desired value
And the temperature value that temperature adjustmemt amount determines so that the difference between the temperature value output of calculating and the temperature value is as far as possible small.When
So, the temperature protection, which calculates, is not limited to PID calculating.It will be understood by those skilled in the art that merely just it is used to illustrate
It is bright, it should not be construed as the limit value to the present invention.
Be computed, obtain temperature value output, between the changing value of temperature value output and the changing value of fuel flow have pair
It should be related to, for example, linear relationship, certainly, is merely just used to illustrate, should not be construed as the limit value to the present invention.According to current
The temperature value output at moment and the temperature value output of previous moment obtain the changing value of temperature value output, and then are known that
The changing value of corresponding fuel flow, and according to previous moment fuel flow, the fuel flow at current time is calculated.
The flame-out limitation protective loop 23 is used to be obtained in fuel flow higher limit and lower limit according to fuel flow value
Between fuel flow output valve, with according to the fuel flow output valve to engine carry out fuel feeding.
The flame-out limitation protective loop 23 can be from high-pressure compressor rate of discharge Wa3Sensor or high-pressure compressor enter
Mouth flow Wa25Sensor obtains the air flow value of combustion chamber, according to fuel flow value and the ratio relation of air flow value, obtains combustion
Oil stream value.For example, obtaining air flow value, and there is fuel flow value and the ratio relation of air flow value, then will obtain
Air flow value be multiplied by ratio relation, obtain fuel flow value.
Fuel flow value and lower limit are carried out taking big operation, then the result operated greatly will be taken to carry out taking small behaviour with higher limit
Make, what is obtained takes small result, i.e. fuel flow output valve.Fuel feeding is carried out to engine according to the fuel flow output valve, now
The rotating speed of engine operating is N2, according to the N2The N being calculated2Dot is that engine speed is control plan, it is, should
N2Dot is controlled device design as the desired value of engine speed.Therefore, the controller based on this design is to meet that surge is abundant
The requirement of the limitation protection of degree, temperature margin and blowoff limit.
In this embodiment, protected as target, directly obtained with the limitation of surge margin, temperature margin and blowoff limit
Meet the fuel flow output valve of above-mentioned target, and fuel feeding is carried out to engine according to the fuel flow output valve.So that can
To obtain engine speed, and obtain N in starting process2Dot control plans, avoid examination manually and gather to obtain this plan
Tedious work.
In another system embodiment of the present invention, also as shown in Fig. 2 the starting process fuel oil control of the aero-engine
System processed, in addition to：Controller 24.
Controller 24, for obtaining the rotating speed acceleration N of engine2Dot desired values, by N2Dot desired values and N2Dot is counted
Difference between calculation value inputs as controller, is calculated, is exported as rotating speed N by differential evolution2, the differential evolution calculate with
Meet N2Dot is instructed and N2Dot follows the difference of signal, N2The phase margin of dot control loop open-loop transfer functions and
N2The cut-off frequency of dot control loop open-loop transfer functions is target, and calculating meets the controller corresponding to the target
Parameter.
Wherein, executing agency carries out fuel feeding according to the fuel flow output valve to engine, and engine is operated and had
Engine speed, the engine speed is obtained, and the rotating speed acceleration value of engine is calculated.Engine speed is calculated to accelerate
The operation of degree can be completed by controller, it is of course also possible to be completed by other mechanisms or device, and obtained and carried out by controller
Subsequent control.
In this embodiment, phase margin and these frequency-domain index of cut-off frequency and this time domain index of tracking error are added
Target after power as optimized algorithm, so that the N obtained by differential evolution algorithm2Dot controllers have good servo with
Track, and have higher stability margin and relatively low loop bandwidth, it is easy to Project Realization.
In an embodiment of the present invention, the controller performs differential evolution calculating and controller parameter is optimized, its
Optimization aim is：
Wherein, e (t) is N2Dot is instructed and N2Dot follows the difference of signal, PM N2Letter is transmitted in the open loop of dot control loops
Several phase margins, Wc N2The cut-off frequency of dot control loop open-loop transfer functions, begin are initial times, and end is knot
Beam time, a, b, c are the weights of three indexs respectively；
Calculated by successive ignition, the N that last time calculates2Dot controller parameters cause desired value J to reach minimum, really
Fixed final N2Dot controller parameters.
In an alternative embodiment of the invention, controller 24 can also be according to fuel flow output valve and compressor delivery pressure
Ps3 ratio calculation obtains oil-gas ratio.And then N is obtained according to the oil-gas ratio2Dot control plans.
Fig. 3 show the structural representation of another embodiment of the starting process fuel control system of aero-engine.Should
Embodiment is acquisition N2The detailed process of dot control plans.
In engine startup operation, various performance parameters are exported, are measured by corresponding sensor.Surge margin limits
Protective loop, temperature margin limitation protective loop and flame-out limitation protective loop processed are respectively positioned in engine electronic control.
Sensor parameters N2、T3、P25、P3It is input in the SMhpc on-time models of surge margin limitation protective loop, calculates
Surge margin value is obtained, it is poor that the surge margin value and desired value SMhpc_cmd are made, and the difference is input to controller Gc2 (s),
The controller form is not limited to PID, after control export surge margin output valve, according to the changing value of surge margin output valve with
Corresponding relation between the changing value of temperature adjustmemt amount obtains temperature adjustmemt amount, then by being input to temperature after saturation nonlinearity link
Spend nargin limitation protective loop, i.e. major loop.The upper limit of the nonlinear element is zero, and lower limit is negative infinite so that surge margin
Limitation protective loop is only just devoted oneself to work when surge margin is less than permissible value.
T4The engine temperature value of sensor collection feeds back to temperature margin limitation protective loop.Temperature margin limitation protection
Loop is using the temperature margin desired value of setting, the engine temperature value obtained and temperature adjustmemt amount as controller Gcl's (s)
Input, the controller form are not limited to PID, obtain temperature value output, and according to the changing value and fuel flow of temperature value output
Changing value between corresponding relation, obtain the fuel flow value at current time, and export to flame-out limitation protective loop.
Wa3The air flow value of sensor collection combustion chamber feeds back to flame-out limitation protective loop.According to fuel flow value and gas
The ratio relation of flow value, obtain fuel flow value.Fuel flow value and lower limit are carried out to take big operation Max, then will be taken big
The result of operation carries out taking small operation Min with higher limit, and what is obtained takes small result, i.e. fuel flow output valve.
The fuel flow output valve is transferred to executing agency, by executing agency according to the fuel flow output valve to starting
Machine carries out fuel feeding, and the rotating speed of now engine operating is N2, directly by accelerometer or pass through output parameter N2Differentiate, obtain
The engine N obtained2Dot outputs are desired N2Dot control plans, and by the N2Dot enters as the desired value of engine speed
Line control unit designs.
Fig. 4 show the structural representation of another embodiment of the starting process fuel control system of aero-engine.Should
Embodiment is according to N2Dot control plans design the detailed process of controller.
N2Dot controllers are differential evolution controller, are inputted as N2Dot desired values (N2Dot_cmd, i.e. N2Dot control meters
Draw) and N2The difference of dot values of feedback, the controller can be PID controller, certainly, however it is not limited to which this, is to realize N2Dot is anti-
Feedback value follows N2Dot desired values, that is, cause N2Dot values of feedback and N2Difference between dot desired values is as far as possible small.Export as fuel oil
Desired value is measured, the amount of fuel desired value is input to Ga (s), and Ga (s) is executing agency's transmission function, exports corresponding amount of fuel,
The amount of fuel is input to G (s), G (s) be engine fuel to the transmission function of rotating speed, export as engine speed N2, the N2Instead
Gs (s) is fed to, Gs (s) is speed probe transmission function, is exported as engine speed N2Measured value, the measured value are output to micro-
Divide link s, export as N2Dot, i.e., as N2Dot values of feedback.Above-mentioned described each controller can be PID controller, also may be used
To be other controllers, as long as the matching of above-mentioned input and output can be realized.
The parameter of controller is optimized by differential evolution algorithm, obtains N2Dot controllers, use following optimization
Target J：
Wherein, e (t) is N2Dot is instructed and N2Dot follows the difference of signal, PM N2Letter is transmitted in the open loop of dot control loops
Several phase margins, Wc N2The cut-off frequency of dot control loop open-loop transfer functions.A, b, c are the power of three indexs respectively
Value.Chosen by rational weights, it is possible to met certain servo tracking precision, stability margin and loop bandwidth simultaneously
Controller parameter.This optimization aim has taken into account tracking error, has reflected the phase angle nargin and and loop bandwidth of stability margin
There is the open-loop cut-off frequency of corresponding relation, small, the loop band that can obtain comparatively tracking error is chosen by rational weights
Wide low while and can makes loop have the controller parameter of sufficiently stable nargin.The flow is iterative process, based on the excellent of design
Change target, when the stability requirement for meeting loop and when reaching set maximum iteration, N can be obtained2Dot optimum controls
Device parameter.
Fig. 5 is a kind of schematic flow sheet of the starting process fuel oil control method of aero-engine.This method includes following
Step：
In step 51, surge margin limitation is carried out according to the surge margin desired value of setting and the surge margin value of calculating
Protection calculates, and obtains surge margin output valve, and according to the corresponding relation of surge margin output valve and temperature adjustmemt amount, obtain temperature
Spend correction.In an alternative embodiment of the invention, the up-and-down boundary value of the temperature adjustmemt amount can also be limited, and is exported small
In the temperature adjustmemt amount equal to 0.
In step 52, entered according to the temperature margin desired value of setting, the engine temperature value obtained and temperature adjustmemt amount
Trip temperature protection calculates, and obtains temperature value output, according to temperature value output and the corresponding relation of fuel flow value, when obtaining current
The fuel flow value at quarter.
In step 53, the fuel flow between fuel flow higher limit and lower limit is obtained according to fuel flow value and exported
Value, to carry out fuel feeding to engine according to the fuel flow output valve.
In this embodiment, protected as target, directly obtained with the limitation of surge margin, temperature margin and blowoff limit
Meet the fuel flow output valve of above-mentioned target, and fuel feeding is carried out to engine according to the fuel flow output valve.So that can
To obtain engine speed, and obtain N in starting process2Dot control plans, avoid examination manually and gather to obtain this plan
Tedious work.
In another embodiment of the invention, this method also includes：Obtain the rotating speed acceleration N of engine2Dot targets
Value, by N2Dot desired values and N2Difference between dot calculated values inputs as controller, is calculated by differential evolution, exports and is
Rotating speed N2, the differential evolution calculated to meet N2Dot is instructed and N2Dot follows the difference of signal, N2Dot control loop open loops
The phase margin and N of transmission function2The cut-off frequency of dot control loop open-loop transfer functions is target, and calculates satisfaction
Controller parameter corresponding to the target.
Wherein, executing agency carries out fuel feeding according to the fuel flow output valve to engine, and engine is operated and had
Engine speed, the engine speed is obtained, and the rotating speed acceleration value of engine is calculated.Engine speed is calculated to accelerate
The operation of degree can be completed by controller, it is of course also possible to be completed by other mechanisms or device, and obtained and carried out by controller
Subsequent control.
In this embodiment, phase margin and these frequency-domain index of cut-off frequency and this time domain index of tracking error are added
Target after power as optimized algorithm so that the N2dot controllers obtained by differential evolution algorithm have good servo with
Track, and have higher stability margin and relatively low loop bandwidth, it is easy to Project Realization.
In another embodiment of the invention, differential evolution calculates and controller parameter is optimized, and its optimization aim is：
Wherein, e (t) is N2Dot is instructed and N2Dot follows the difference of signal, PM N2Letter is transmitted in the open loop of dot control loops
Several phase margins, Wc N2The cut-off frequency of dot control loop open-loop transfer functions, begIn is initial time, and end is end
Time, a, b, c are the weights of three indexs respectively；
Calculated by successive ignition, the N that last time calculates2Dot controller parameters cause desired value J to reach minimum, really
Fixed final N2Dot controller parameters.
In another embodiment of the invention, this method also includes：According to fuel flow output valve and blower outlet pressure
Power Ps3 ratio calculation obtains oil-gas ratio.
So far, the present invention is described in detail.In order to avoid the design of the masking present invention, it is public that this area institute is not described
Some details known.Those skilled in the art as described above, can be appreciated how to implement technology disclosed herein completely
Scheme.
The method and device of the present invention may be achieved in many ways.For example, can by software, hardware, firmware or
Person's software, hardware, firmware any combinations come realize the present invention method and device.The step of for methods described it is above-mentioned
Order is not limited to order described in detail above merely to illustrate, the step of method of the invention, unless with other sides
Formula illustrates.In addition, in certain embodiments, the present invention can be also embodied as recording program in the recording medium, these
Program includes being used for the machine readable instructions for realizing the method according to the invention.Thus, the present invention also covering storage is used to perform
The recording medium of the program of the method according to the invention.
Although some specific embodiments of the present invention are described in detail by example, the skill of this area
Art personnel it should be understood that above example merely to illustrating, the scope being not intended to be limiting of the invention.The skill of this area
Art personnel to above example it should be understood that can modify without departing from the scope and spirit of the present invention.This hair
Bright scope is defined by the following claims.
Claims (14)
1. a kind of starting process fuel oil control method of aero-engine, including：
Surge margin limitation protection is carried out according to the surge margin desired value of setting and the surge margin value of calculating to calculate, and is obtained
Surge margin output valve, and according to the corresponding relation of surge margin output valve and temperature adjustmemt amount, obtain temperature adjustmemt amount；
Temperature protection meter is carried out according to the temperature margin desired value of setting, the engine temperature value obtained and temperature adjustmemt amount
Calculate, obtain temperature value output, according to temperature value output and the corresponding relation of fuel flow value, obtain the fuel flow at current time
Value；
Fuel flow output valve between fuel flow higher limit and lower limit is obtained according to fuel flow value, with according to
Fuel flow output valve carries out fuel feeding to engine.
2. the starting process fuel oil control method of aero-engine according to claim 1, in addition to：
Obtain the rotating speed acceleration N of engine2Dot desired values, by N2Dot desired values and N2Difference conduct between dot calculated values
Controller inputs, and is calculated, is exported as rotating speed N by differential evolution2, the differential evolution calculated to meet N2Dot instruct with
N2Dot follows the difference of signal, N2The phase margin and N of dot control loop open-loop transfer functions2Dot control loop open loops
The cut-off frequency of transmission function is target, and calculating meets the controller parameter corresponding to the target.
3. the starting process fuel oil control method of aero-engine according to claim 1 or claim 2, including：
The up-and-down boundary value of the temperature adjustmemt amount is limited, and exports the temperature adjustmemt amount less than or equal to 0.
4. the starting process fuel oil control method of aero-engine according to claim 2, including：
Differential evolution calculates and controller parameter is optimized, and its optimization aim is：
<mrow>
<mi>J</mi>
<mo>=</mo>
<msubsup>
<mo>&Integral;</mo>
<mrow>
<mi>b</mi>
<mi>e</mi>
<mi>g</mi>
<mi>i</mi>
<mi>n</mi>
</mrow>
<mrow>
<mi>e</mi>
<mi>n</mi>
<mi>d</mi>
</mrow>
</msubsup>
<mrow>
<mo>(</mo>
<mi>a</mi>
<mo>|</mo>
<mrow>
<mi>e</mi>
<mrow>
<mo>(</mo>
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<mo>)</mo>
</mrow>
</mrow>
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<mi>d</mi>
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Wherein, e (t) is N2Dot is instructed and N2Dot follows the difference of signal, PM N2Dot control loop open-loop transfer functions
Phase margin, Wc N2The cut-off frequency of dot control loop open-loop transfer functions, begin is initial time, at the end of end is
Between, a, b, c are the weights of three indexs respectively；
Calculated by successive ignition, the N that last time calculates2Dot controller parameters cause desired value J to reach minimum, it is determined that finally
N2Dot controller parameters.
5. the starting process fuel oil control method of aero-engine according to claim 1 or claim 2, including：
The temperature T before high-pressure turbine4Sensor or engine exhaust temperature EGT sensors obtain engine temperature value.
6. the starting process fuel oil control method of aero-engine according to claim 1 or claim 2, including：
The gas of combustion chamber is obtained from high-pressure compressor rate of discharge Wa3 sensors or high-pressure compressor inlet flow rate Wa25 sensors
Flow value, according to fuel flow value and the ratio relation of air flow value, obtain fuel flow value.
7. the starting process fuel oil control method of aero-engine according to claim 1 or claim 2, including：
Oil-gas ratio is obtained according to fuel flow output valve and compressor delivery pressure Ps3 ratio calculation.
8. a kind of starting process fuel control system of aero-engine, including：Surge margin limitation protective loop, temperature margin
Limit protective loop and flame-out limitation protective loop；
The surge margin limitation protective loop is used for according to the surge margin desired value of setting and the surge margin value of calculating
Carry out surge margin limitation protection to calculate, obtain surge margin output valve, and according to surge margin output valve and temperature adjustmemt amount
Corresponding relation, obtain temperature adjustmemt amount；
Temperature margin limitation protective loop be used for the temperature margin desired value according to setting, the engine temperature value obtained with
It is corresponding with fuel flow value according to temperature value output and temperature adjustmemt amount carries out temperature protection calculating, obtains temperature value output
Relation, obtain the fuel flow value at current time；
The flame-out limitation protective loop is used to be obtained between fuel flow higher limit and lower limit according to fuel flow value
Fuel flow output valve, to carry out fuel feeding to engine according to the fuel flow output valve.
9. the starting process fuel control system of aero-engine according to claim 8, in addition to：
Controller, for obtaining the rotating speed acceleration N of engine2Dot desired values, by N2Dot desired values and N2Dot calculated values it
Between difference as controller input, calculated, exported as rotating speed N by differential evolution2, the differential evolution calculated to meet
N2Dot is instructed and N2Dot follows the difference of signal, N2The phase margin and N of dot control loop open-loop transfer functions2Dot is controlled
The cut-off frequency of loop open-loop transfer function processed is target, and calculating meets the controller parameter corresponding to the target.
10. the starting process fuel control system of aero-engine according to claim 8 or claim 9, including：
The surge margin limitation protective loop limits the up-and-down boundary value of the temperature adjustmemt amount, and exports and be less than or equal to 0
Temperature adjustmemt amount.
11. the starting process fuel control system of aero-engine according to claim 9, including：
The controller performs differential evolution calculating and controller parameter is optimized, and its optimization aim is：
<mrow>
<mi>J</mi>
<mo>=</mo>
<msubsup>
<mo>&Integral;</mo>
<mrow>
<mi>b</mi>
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<mi>i</mi>
<mi>n</mi>
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</mrow>
</msubsup>
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<mo>)</mo>
</mrow>
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<mo>+</mo>
<mi>b</mi>
<mo>/</mo>
<mi>P</mi>
<mi>M</mi>
<mo>+</mo>
<mi>c</mi>
<mi>W</mi>
<mi>c</mi>
<mo>)</mo>
</mrow>
<mi>d</mi>
<mi>t</mi>
</mrow>
Wherein, e (t) is N2Dot is instructed and N2Dot follows the difference of signal, PM N2Dot control loop open-loop transfer functions
Phase margin, Wc N2The cut-off frequency of dot control loop open-loop transfer functions, begin is initial time, at the end of end is
Between, a, b, c are the weights of three indexs respectively；
Calculated by successive ignition, the N that last time calculates2Dot controller parameters cause desired value J to reach minimum, it is determined that finally
N2Dot controller parameters.
12. the starting process fuel control system of aero-engine according to claim 8 or claim 9, including：
Temperature margin limitation protective loop temperature T before high-pressure turbine4Sensor or engine exhaust temperature EGT sensors
Obtain engine temperature value.
13. the starting process fuel control system of aero-engine according to claim 8 or claim 9, including：
The flame-out protective loop that limits is from high-pressure compressor rate of discharge Wa3 sensors or high-pressure compressor inlet flow rate Wa25
Sensor obtains the air flow value of combustion chamber, according to fuel flow value and the ratio relation of air flow value, obtains fuel flow value.
14. the starting process fuel control system of aero-engine according to claim 9, including：
The controller obtains oil-gas ratio according to fuel flow output valve and compressor delivery pressure Ps3 ratio calculation.
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