CN109595079A - Aero-engine transition state fuel oil control method, system and aero-engine - Google Patents
Aero-engine transition state fuel oil control method, system and aero-engine Download PDFInfo
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- CN109595079A CN109595079A CN201710912852.1A CN201710912852A CN109595079A CN 109595079 A CN109595079 A CN 109595079A CN 201710912852 A CN201710912852 A CN 201710912852A CN 109595079 A CN109595079 A CN 109595079A
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- Prior art keywords
- engine
- aero
- compressor
- pressure
- oil
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
Abstract
The present invention relates to a kind of aero-engine transition state fuel oil control method, system and aero-engines.Wherein, the fuel feeding formula that aero-engine transition state fuel oil control method provides according to the present invention carries out oil-gas ratio control, increases stagnation pressure P after compressor3As transition state fuel control parameter, the oil-gas ratio control law for increasing control parameter is given simultaneously, improve the accuracy of control, efficiently solve the problems, such as that practical oil-gas ratio is higher than control oil-gas ratio, it avoids generating stall or the generation of surge problems, improves the stability and reliability of the aero-engine transition state course of work.
Description
Technical field
The present invention relates to aero-engine technology field more particularly to a kind of aero-engine transition state fuel oil controlling parties
Method, system and aero-engine.
Background technique
In aero-engine technology field, transition state refers to when aero-engine is started by stationary state to idling rating
Or the process of another stable state is transitioned by more than slow train and slow train one stable state, to guarantee aero-engine dimension
Hold some state or by a status transition to another state, need to adjust fuel supply volume in real time, aviation
Engine transition state fuel oil control mode is controlled by oil-gas ratio.
Air mass flow W after compressor3It is represented by following formula:
Wherein: K-constant；P3Stagnation pressure after-compressor；T3Total moisture content after-compressor；
Area of section after A-compressor；Ma- Mach number；Q (Ma)-flow function.
Due to static pressure P after compressorS3Measurement is convenient, therefore generally by static pressure P after compressorS3As control variable, in this way
(1) formula converts are as follows:
If engine operating point under each revolving speed is constant, Mach number is believed that constant, T3After being similar to compressor
The function of static pressure Ps3, therefore, static pressure Ps3 is W after compressor3Monotropic function, the air mass flow of blower outlet can be represented
W3。
Consider to convert by engine intake temperature and pressure, be expressed as following formula by oil-gas ratio control mode:
Wherein: WfFuel flow；T2Engine intake temperature；- high-pressure compressor corrected spool speed,For
The fuel supply rate curve function measured in the case that Mach number is approximate constant under experimental state.
This fuel system can guarantee engine under any flying condition, and oil-gas ratio is with high-pressure compressor corrected spool speed
By given rule variation.
As shown in Figure 1, normally being accelerated under a certain revolving speed relative to steady operation point A when engine normally accelerates
Operating point B, engine press point pressure P3B, air mass flow W3BCorresponding expected oil-gas ratio fuel feeding.
But since the factors such as change of external conditions or engine itself performance or control deviation influence, when engine plus
Operating point C, C point pressure P are accelerated to when fast under this revolving speed3CGreater than P3B, but air mass flow W3CLess than W3B, therefore by above-mentioned
Oil-gas ratio control mode, C point pressure is high, and fuel flow increases, but air mass flow not only reduces without increasing instead, therefore practical
Oil-gas ratio increases, and turbine inlet temperature increases, and operating point can be accelerated mobile to stall margin, if compressor surge nargin is inadequate
Greatly, engine is easy stall even into asthma.
Leading to the problem of the reason of such be this oil-gas ratio control mode is that approximate blower outlet Mach number is constant, but works as
Engine deviates from original active line for some reason, and Mach number can change, static pressure P after compressorS3It is no longer air stream
The monotropic function of amount, therefore this just will appear practical oil-gas ratio and is higher than control oil-gas ratio problem.
Summary of the invention
To overcome the above technological deficiency, the technical problem to be solved by the present invention is to provide a kind of aero-engine transition state fuel oils
Control method, system and aero-engine can be improved the stability and reliability of the aero-engine transition state course of work.
In order to solve the above technical problems, the present invention provides a kind of aero-engine transition state fuel oil control method, the party
Method carries out oil-gas ratio control according to the following formula:
Wherein, WfFor fuel flow；P3For stagnation pressure after compressor；PS3For static pressure after compressor；T2For engine intake temperature
Degree；For high-pressure compressor corrected spool speed；For the fuel supply rate curve function measured under experimental state.
Further,Wherein, N is engine speed.
The present invention also provides a kind of aero-engine fuel control systems comprising testing agency and controller, detection
Mechanism is for detecting stagnation pressure P after compressor3, static pressure P after compressorS3, engine intake temperature T2And engine speed N and anti-
It feeds controller, controller for carrying out oil-gas ratio control according to the following formula under transition state:
Wherein, WfFor fuel flow；P3For stagnation pressure after compressor；PS3For static pressure after compressor；T2For engine intake temperature
Degree；For the high-pressure compressor corrected spool speed obtained according to engine speed N conversion；To be surveyed under experimental state
The fuel supply rate curve function obtained.
Further, testing agency includes that the total static pressure being arranged in high-pressure compressor export orientation blade passage is felt
Portion, for detecting stagnation pressure P after compressor3With static pressure P after compressorS3。
It further, further include the wind blade being arranged in high-pressure compressor export orientation blade passage, wind blade
It is symmetrical set with the guide vane in high-pressure compressor export orientation blade passage.
The present invention also provides a kind of aero-engines comprising above-mentioned aero-engine fuel control system.
As a result, based on the above-mentioned technical proposal, aero-engine transition state fuel oil control method and system of the present invention are by setting
Corrected parameter is set, efficiently solves the problems, such as that practical oil-gas ratio is higher than control oil-gas ratio, avoids generating stall or surge problems
Occur, improves the stability and reliability of the aero-engine transition state course of work.Aero-engine provided by the invention
Correspondingly there are above-mentioned advantageous effects.
Detailed description of the invention
The drawings described herein are used to provide a further understanding of the present invention, constitutes part of this application, this hair
Bright illustrative embodiments and their description for explaining only the invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the changing rule schematic diagram of aero-engine transition state operating point；
Fig. 2 is the structural schematic diagram of wind blade in aero-engine fuel control system of the present invention；
Fig. 3 is the setting position view of total static pressure detector probe in aero-engine fuel control system of the present invention；
Fig. 4 is the operation principle schematic diagram of controller in aero-engine fuel control system of the present invention.
Each appended drawing reference respectively represents:
1, guide vane；2, wind blade；3, combustion box；4, total static pressure detector probe；5, controller.
Specific embodiment
Below by drawings and examples, technical scheme of the present invention will be described in further detail.
A specific embodiment of the invention be for the ease of to design of the invention, it is solved the technical issues of, constitute skill
The technical characteristic and bring technical effect of art scheme have further description.It should be noted that for these embodiment party
The explanation of formula does not constitute a limitation of the invention simultaneously.In addition, technology involved in the embodiment of present invention described below is special
Sign can be combined with each other as long as they do not conflict with each other.
It is higher than control oil-gas ratio to solve the problems, such as to occur practical oil-gas ratio it is necessary to considering high-pressure compressor exit Mach number
Influence to air mass flow increases Mach number as transition state fuel control parameter, improves the accuracy of control.
Q (Ma)=Ma (1+0.2Ma2)-3…………………(4)
(4) formula is substituted into (2) formula
Since Mach number Ma is not parameter measured directly, increase stagnation pressure P after compressor3As control variable, and
Static pressure P after compressorS3Together, it presses formula and calculates blower outlet Mach number.
(6) formula is substituted into (5) formula
Therefore accordingly consider that the oil-gas ratio control mode of Mach number is expressed as
Wherein, WfFor fuel flow；P3For stagnation pressure after compressor；PS3For static pressure after compressor；T2For engine intake temperature
Degree；For the high-pressure compressor corrected spool speed obtained according to engine speed N conversion；To be surveyed under experimental state
The fuel supply rate curve function obtained.
Aero-engine transition state fuel oil control method of the present invention increases stagnation pressure P after compressor3As transition state fuel oil
Control parameter, while the oil-gas ratio control law for increasing control parameter is given, the accuracy of control is improved, is efficiently solved
Practical oil-gas ratio is higher than control oil-gas ratio problem, avoids generating stall or the generation of surge problems, improves aero-engine mistake
Cross the stability and reliability of the state course of work.Wherein, high-pressure compressor corrected spool speed can be converted by engine speed N
Out, in a preferred embodiment,
Invention accordingly provides a kind of aero-engine fuel control systems, as shown in Figure 2 to 4, aeroplane engine
Machine fuel control system includes testing agency and controller 5, and testing agency is for detecting stagnation pressure P after compressor3, it is quiet after compressor
Press PS3, engine intake temperature T2And engine speed N and controller 5 being fed back to, controller 5 is used for the basis under transition state
Following formula carries out oil-gas ratio control:
Wherein, WfFor fuel flow；P3For stagnation pressure after compressor；PS3For static pressure after compressor；T2For engine intake temperature
Degree；For the high-pressure compressor corrected spool speed obtained according to engine speed N conversion；To be surveyed under experimental state
The fuel supply rate curve function obtained.
Aero-engine fuel control system of the present invention increases stagnation pressure P after compressor3It controls and joins as transition state fuel oil
Number, while controller 5 increases the oil-gas ratio control law of control parameter, improves the accuracy of control, efficiently solves reality
Oil-gas ratio is higher than control oil-gas ratio problem, avoids generating stall or the generation of surge problems, improves aero-engine transition state
The stability and reliability of the course of work.Wherein it is preferred to which as shown in figure 3, testing agency includes that setting goes out in high-pressure compressor
Total static pressure detector probe 4 in mouthful guide vane runner, for detecting stagnation pressure P after compressor3With static pressure P after compressorS3.Total static pressure
Detector probe 4 can be punched by the wall surface in combustion box 3 to place, and selected in high-pressure compressor export orientation blade passage
Stagnation pressure P after interior measurement compressor3With static pressure P after compressorS3, detection is accurate, and exploitativeness is high.
Mach number is small after compressor, P3/PS3Close to 1, it is unable to satisfy the requirement of control parameter, due to high-pressure compressor
Export orientation blade passage inner area is minimum, and Mach number is higher, and between engine ignition and maximum rating, Mach number exists
Between 0.15-0.2, in order to further increase Mach number, Measurement channel is improved, in a preferred embodiment, such as Fig. 2 institute
Showing, aero-engine fuel control system further includes the wind blade 2 being arranged in high-pressure compressor export orientation blade passage,
Wind blade 2 is symmetrical set with the guide vane 1 in high-pressure compressor export orientation blade passage, reduces discharge area,
Wind speed V3Increase, further increases Mach number, make P3/PS3Meet control accuracy requirement.
The present invention also provides a kind of aero-engines comprising above-mentioned aero-engine fuel control system.Due to
Aero-engine fuel control system of the present invention can be improved the stability and reliability of the transition state course of work, correspondingly, this
Invention aero-engine also correspondingly has above-mentioned advantageous effects, and details are not described herein.
The embodiment combined above is described in detail embodiments of the present invention, but the present invention is not limited to be retouched
The embodiment stated.For a person skilled in the art, in the case where not departing from the principle and substance of the present invention spirit
A variety of variations, modification, equivalence replacement and modification is carried out to these embodiments to still fall within protection scope of the present invention.
Claims (6)
1. a kind of aero-engine transition state fuel oil control method, which is characterized in that carry out oil-gas ratio control according to the following formula:
Wherein, WfFor fuel flow；P3For stagnation pressure after compressor；PS3For static pressure after compressor；T2For engine intake temperature；For high-pressure compressor corrected spool speed；For the fuel supply rate curve function measured under experimental state.
2. aero-engine transition state fuel oil control method according to claim 1, which is characterized in thatWherein, N is engine speed.
3. a kind of aero-engine fuel control system, which is characterized in that including testing agency and controller (5), the detection
Mechanism is for detecting stagnation pressure P after compressor3, static pressure P after compressorS3, engine intake temperature T2And engine speed N and anti-
It feeds the controller (5), the controller (5) for carrying out oil-gas ratio control according to the following formula under transition state:
Wherein, WfFor fuel flow；P3For stagnation pressure after compressor；PS3For static pressure after compressor；T2For engine intake temperature；For the high-pressure compressor corrected spool speed obtained according to engine speed N conversion；It is measured under experimental state
Fuel supply rate curve function.
4. aero-engine fuel control system according to claim 3, which is characterized in that the testing agency includes setting
Total static pressure detector probe (4) in high-pressure compressor export orientation blade passage is set, for detecting stagnation pressure P after compressor3And pressure
Static pressure P after mechanism of qiS3。
5. aero-engine fuel control system according to claim 4, which is characterized in that further include being arranged in the height
Press the wind blade (2) in blower outlet guide vane runner, the wind blade (2) and the high-pressure compressor outlet guide
Guide vane (1) into blade passage is symmetrical set.
6. a kind of aero-engine, which is characterized in that including the described in any item aero-engine fuel oil controls of claim 3~5
System processed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710912852.1A CN109595079A (en) | 2017-09-30 | 2017-09-30 | Aero-engine transition state fuel oil control method, system and aero-engine |
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| CN201710912852.1A CN109595079A (en) | 2017-09-30 | 2017-09-30 | Aero-engine transition state fuel oil control method, system and aero-engine |
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| CN109595079A true CN109595079A (en) | 2019-04-09 |
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| CN201710912852.1A Pending CN109595079A (en) | 2017-09-30 | 2017-09-30 | Aero-engine transition state fuel oil control method, system and aero-engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114676530A (en) * | 2022-04-16 | 2022-06-28 | 中国航发沈阳发动机研究所 | Method for designing transition state working line of gas turbine engine |
| CN114837821A (en) * | 2022-04-29 | 2022-08-02 | 中国航发沈阳发动机研究所 | Self-adaptive adjusting method and system for ground starting oil supply rule of aircraft engine |
-
2017
- 2017-09-30 CN CN201710912852.1A patent/CN109595079A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114676530A (en) * | 2022-04-16 | 2022-06-28 | 中国航发沈阳发动机研究所 | Method for designing transition state working line of gas turbine engine |
| CN114837821A (en) * | 2022-04-29 | 2022-08-02 | 中国航发沈阳发动机研究所 | Self-adaptive adjusting method and system for ground starting oil supply rule of aircraft engine |
| CN114837821B (en) * | 2022-04-29 | 2023-07-07 | 中国航发沈阳发动机研究所 | Self-adaptive adjustment method and system for ground start oil supply law of aero-engine |
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Application publication date: 20190409 |
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