CN114233512A - Aircraft engine thrust consistency debugging and working state control method thereof - Google Patents
Aircraft engine thrust consistency debugging and working state control method thereof Download PDFInfo
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- CN114233512A CN114233512A CN202111597789.XA CN202111597789A CN114233512A CN 114233512 A CN114233512 A CN 114233512A CN 202111597789 A CN202111597789 A CN 202111597789A CN 114233512 A CN114233512 A CN 114233512A
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- aircraft engine
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- rotating speed
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
- F02K1/16—Control or regulation conjointly with another control
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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
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
One aspect of the present application provides a method for debugging thrust consistency of an aircraft engine, including: constructing an aircraft engine nozzle throat area control law based on the rotating speed of a low-pressure rotor of an aircraft engine; and under the constructed throat area control law of the jet pipe of the aircraft engine, the rotating speed of a low-pressure rotor of the aircraft engine is converted, and if the pressure ratio of the aircraft engine does not accord with the standard pressure ratio value, the throat area control law of the jet pipe of the aircraft engine is corrected until the pressure ratio of the aircraft engine accords with the standard pressure ratio value. In another aspect, a method for controlling the operating condition of an aircraft engine is provided, including: constructing a low-pressure rotor rotating speed control law of the aircraft engine based on the position of an accelerator lever of the aircraft engine; and controlling the working state of the aircraft engine according to the low-pressure rotor rotating speed control law of the aircraft engine.
Description
Technical Field
The application belongs to the technical field of aircraft engine working state control, and particularly relates to aircraft engine thrust consistency debugging and a working state control method thereof.
Background
The situation that the thrust difference of a left engine and a right engine is large often occurs when the airplane provided with double engines is assembled, and in some situations, the left engine and the right engine have to be controlled separately, so that the operation burden of a pilot is increased seriously, the fuel consumption is increased, and even danger is caused.
The thrust of most aircraft engines is mainly determined by air flow and exhaust speed, wherein the main factor influencing the air flow is the converted rotating speed of a low-pressure rotor of the aircraft engine, the current working state of the aircraft engine is mostly controlled according to the rotating speed of an accelerator lever and a high-pressure rotor of the aircraft engine, the accurate control on the thrust of the aircraft engine is difficult to realize, in addition, the main factor influencing the exhaust speed is the throat area of an aircraft engine spray pipe, when the aircraft engine leaves a factory, the throat area of the aircraft engine spray pipe is not corrected in a targeted manner, the accurate control on the thrust of the aircraft engine is also influenced, in addition, in the processing and manufacturing process of the aircraft engine, size deviation is inevitably introduced, friction damage of different degrees occurs in subsequent use, and large difference possibly exists among individuals of the aircraft engine, accurate control of aircraft engine thrust may also be affected.
The present application has been made in view of the above-mentioned technical drawbacks.
Disclosure of Invention
The present application aims to provide a method for debugging the thrust consistency of an aircraft engine and for controlling the operating conditions thereof, so as to overcome or alleviate at least one of the technical drawbacks of the known prior art.
The technical scheme of the application is as follows:
in one aspect, a method for debugging the thrust consistency of an aircraft engine is provided, which includes:
constructing an aircraft engine nozzle throat area control law based on the rotating speed of a low-pressure rotor of an aircraft engine;
and under the constructed throat area control law of the jet pipe of the aircraft engine, the rotating speed of a low-pressure rotor of the aircraft engine is converted, and if the pressure ratio of the aircraft engine does not accord with the standard pressure ratio value, the throat area control law of the jet pipe of the aircraft engine is corrected until the pressure ratio of the aircraft engine accords with the standard pressure ratio value.
According to at least one embodiment of the present application, in the aircraft engine thrust consistency debugging method, the method further includes:
and under the corrected control law of the throat area of the jet pipe of the aircraft engine, converting the rotating speed of a low-pressure rotor of the aircraft engine, and if the thrust of the aircraft engine does not accord with the standard thrust value, further correcting the control law of the throat area of the jet pipe of the aircraft engine until the thrust of the aircraft engine accords with the standard thrust value.
According to at least one embodiment of the application, in the aircraft engine thrust consistency debugging method, when the thrust of the aircraft engine does not meet the standard thrust value, the control law of the throat area of the nozzle of the aircraft engine is further corrected, and the correction is performed within the range of the operating point of the fan of the aircraft engine.
According to at least one embodiment of the application, in the aircraft engine thrust consistency debugging method, the operating point of the aircraft engine fan is characterized by W1R/pif;
wherein the content of the first and second substances,
W1R is aircraft engine air flow;
pif is the aircraft engine fan pressure ratio.
In another aspect, a method for controlling the operating condition of an aircraft engine is provided, including:
constructing a low-pressure rotor rotating speed control law of the aircraft engine based on the position of an accelerator lever of the aircraft engine;
and controlling the working state of the aircraft engine according to the low-pressure rotor rotating speed control law of the aircraft engine.
The application has at least the following beneficial technical effects:
on one hand, the method for debugging the thrust consistency of the aircraft engine is provided, which considers the main factors influencing the thrust of the aircraft engine, namely the rotating speed of a low-pressure rotor of the aircraft engine and the area of a nozzle throat, constructs a control law of the area of the nozzle throat of the aircraft engine based on the rotating speed of the low-pressure rotor of the aircraft engine, transforms the rotating speed of the low-pressure rotor of the aircraft engine, and corrects the control law of the area of the nozzle throat of the aircraft engine until the pressure ratio of the aircraft engine meets the standard value of the pressure ratio, so that the thrust consistency debugging of the aircraft engine is realized, and conditions are provided for the accurate control of the thrust of the aircraft engine.
On the other hand, the method for controlling the working state of the aircraft engine is characterized in that a low-pressure rotor rotating speed control law of the aircraft engine is constructed based on the position of an accelerator lever of the aircraft engine, the working state of the aircraft engine is controlled, the airplane engine accelerator lever position-low-pressure rotor rotating speed control scheme replaces the airplane engine accelerator lever position-high-pressure rotor rotating speed scheme to control the working state of the aircraft engine, and a more direct relation between the position of the accelerator lever of the aircraft engine and the air flow is established, so that the thrust of the aircraft engine can be controlled more accurately.
Drawings
FIG. 1 is a schematic diagram of a method for debugging thrust consistency of an aircraft engine provided by an embodiment of the present application;
FIG. 2 is a schematic illustration of an aircraft engine nozzle throat area control law provided by an embodiment of the present application;
FIG. 3 is a schematic illustration of an aircraft engine fan operating point range provided by an embodiment of the present application;
FIG. 4 is a schematic illustration of an aircraft engine fan inlet guide vane angle control law provided by an embodiment of the present application.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The word "comprising" or "comprises", and the like, when used in the description of this application, is intended to indicate that the subject matter presented in front of the word covers the parts listed after the word, but not excluding others.
The present application is described in further detail below with reference to fig. 1 to 4.
In one aspect, a method for debugging the thrust consistency of an aircraft engine is provided, which includes:
constructing an aircraft engine nozzle throat area control law based on the aircraft engine low-pressure rotor rotating speed, and specifically constructing the aircraft engine nozzle throat area control law according to engineering experience, wherein A8 represents the aircraft engine nozzle throat area, and n1R represents the aircraft engine low-pressure rotor rotating speed, as shown in FIG. 2;
and under the constructed throat area control law of the jet pipe of the aircraft engine, the rotating speed of a low-pressure rotor of the aircraft engine is converted, and if the pressure ratio of the aircraft engine does not accord with the standard pressure ratio value, namely the pressure ratio does not deviate greatly from the standard pressure ratio value, the throat area control law of the jet pipe of the aircraft engine is corrected until the pressure ratio of the aircraft engine accords with the standard pressure ratio value.
For the aircraft engine thrust consistency debugging method disclosed in the above embodiment, as can be understood by those skilled in the art, the aircraft engine low-pressure rotor rotation speed and the nozzle throat area, which are main factors affecting the aircraft engine thrust, are considered, based on the aircraft engine low-pressure rotor rotation speed, an aircraft engine nozzle throat area control law is constructed, the aircraft engine low-pressure rotor rotation speed is converted, and the aircraft engine nozzle throat area control law is corrected until the pressure ratio of the aircraft engine meets the pressure ratio standard value, so that the aircraft engine thrust consistency debugging is realized, and conditions are provided for the accurate control of the aircraft engine thrust.
In some alternative embodiments, in the aircraft engine thrust consistency debugging method, the pressure ratio standard value is empirically given, and may also be determined from a large number of aircraft engine statistical data.
In some optional embodiments, in the method for debugging thrust consistency of an aircraft engine, the method further includes:
and under the corrected control law of the throat area of the jet pipe of the aircraft engine, converting the rotating speed of a low-pressure rotor of the aircraft engine, and if the thrust of the aircraft engine does not accord with a standard thrust value, namely the thrust of the aircraft engine has a larger deviation from the standard thrust value, further correcting the control law of the throat area of the jet pipe of the aircraft engine until the thrust of the aircraft engine accords with the standard thrust value.
For the aircraft engine thrust consistency debugging method disclosed in the above embodiment, it can be understood by those skilled in the art that when the thrust of the aircraft engine does not meet the standard thrust value, the throat area control law of the aircraft engine nozzle is further modified until the thrust of the aircraft engine meets the standard thrust value, so as to ensure the consistency of the thrust of the aircraft engine and provide a reliable basis for the accurate control of the thrust of the aircraft engine.
In some alternative embodiments, in the aircraft engine thrust consistency debugging method, the thrust standard value is empirically given, and may also be determined from a large amount of aircraft engine statistical data.
In some optional embodiments, in the method for debugging thrust consistency of an aircraft engine, the method further includes:
when the thrust of the aircraft engine does not accord with the standard thrust value, the throat area control law of the aircraft engine nozzle is further corrected, and correction is carried out within the range of the operating point of the aircraft engine fan so as to control the surge margin of the aircraft engine and ensure the working stability of the aircraft engine fan.
In some optional embodiments, in the aircraft engine thrust consistency debugging method, an aircraft engine fan operating point is characterized by W1R/pif;
wherein the content of the first and second substances,
W1R is aircraft engine air flow;
pif is the aircraft engine fan pressure ratio.
In some alternative embodiments, in the aircraft engine thrust consistency debugging method, the range of the aircraft engine fan operating point is empirically given, or can be determined from a large number of aircraft engine statistical data, as shown in fig. 3.
In some optional embodiments, in the aircraft engine thrust consistency debugging method, in order to ensure the effect of debugging the aircraft engine thrust consistency, before debugging, design correction is performed on other parameters affecting the aircraft engine thrust, such as the aircraft engine high-pressure turbine guider area, the aircraft engine low-pressure turbine guider area, and the aircraft engine fan inlet guide blade angle control law, as shown in fig. 4, where a1 represents the aircraft engine fan inlet guide blade angle size.
In another aspect, a method for controlling the operating condition of an aircraft engine is provided, including:
constructing a low-pressure rotor rotating speed control law of the aircraft engine based on the position of an accelerator lever of the aircraft engine;
and controlling the working state of the aircraft engine according to the low-pressure rotor rotating speed control law of the aircraft engine.
For the method for controlling the working state of the aircraft engine disclosed in the above embodiment, a person skilled in the art can understand that a law for controlling the rotating speed of a low-pressure rotor of the aircraft engine is constructed based on the position of an accelerator lever of the aircraft engine, the working state of the aircraft engine is controlled, the scheme of the position of the accelerator lever of the aircraft engine and the rotating speed of the high-pressure rotor is replaced by the scheme of the position of the accelerator lever of the aircraft engine and the rotating speed of the low-pressure rotor, and a direct relation between the position of the accelerator lever of the aircraft engine and the air flow is established, so that the thrust of the aircraft engine can be controlled more accurately.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (5)
1. An aircraft engine thrust consistency debugging method is characterized by comprising the following steps:
constructing an aircraft engine nozzle throat area control law based on the rotating speed of a low-pressure rotor of an aircraft engine;
and under the constructed throat area control law of the jet pipe of the aircraft engine, the rotating speed of a low-pressure rotor of the aircraft engine is converted, and if the pressure ratio of the aircraft engine does not accord with the standard pressure ratio value, the throat area control law of the jet pipe of the aircraft engine is corrected until the pressure ratio of the aircraft engine accords with the standard pressure ratio value.
2. The aircraft engine thrust consistency debugging method of claim 1,
further comprising:
and under the corrected control law of the throat area of the jet pipe of the aircraft engine, converting the rotating speed of a low-pressure rotor of the aircraft engine, and if the thrust of the aircraft engine does not accord with the standard thrust value, further correcting the control law of the throat area of the jet pipe of the aircraft engine until the thrust of the aircraft engine accords with the standard thrust value.
3. The aircraft engine thrust consistency debugging method of claim 2,
and when the thrust of the aircraft engine does not accord with the standard thrust value, further correcting the control law of the throat area of the jet pipe of the aircraft engine, and correcting the control law within the range of the working point of the fan of the aircraft engine.
4. The aircraft engine thrust consistency debugging method of claim 3,
the fan operating point of the aircraft engine is characterized by W1R/pif;
wherein the content of the first and second substances,
W1R is aircraft engine air flow;
pif is the aircraft engine fan pressure ratio.
5. An aircraft engine operating condition control method, comprising:
constructing a low-pressure rotor rotating speed control law of the aircraft engine based on the position of an accelerator lever of the aircraft engine;
and controlling the working state of the aircraft engine according to the low-pressure rotor rotating speed control law of the aircraft engine.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111597789.XA CN114233512B (en) | 2021-12-24 | 2021-12-24 | Aircraft engine thrust consistency debugging and working state control method thereof |
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| CN202111597789.XA CN114233512B (en) | 2021-12-24 | 2021-12-24 | Aircraft engine thrust consistency debugging and working state control method thereof |
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| CN114233512B CN114233512B (en) | 2023-03-14 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117725680A (en) * | 2023-12-21 | 2024-03-19 | 中国航空研究院 | Wide-speed-range self-adaptive pneumatic trapped vortex air inlet channel design method |
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