CN114233512B - 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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- CN114233512B CN114233512B CN202111597789.XA CN202111597789A CN114233512B CN 114233512 B CN114233512 B CN 114233512B CN 202111597789 A CN202111597789 A CN 202111597789A CN 114233512 B CN114233512 B CN 114233512B
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- aircraft engine
- thrust
- control law
- throat area
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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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- Combustion & Propulsion (AREA)
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- 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 an 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 main factor influencing the air flow is the conversion 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, and the accurate control on the thrust of the aircraft engine is difficult to realize.
The present application has been made in view of the above-mentioned technical drawbacks.
Disclosure of Invention
The object of the present application is 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 the aircraft engine air flow;
pif is the aircraft engine fan pressure ratio.
In another aspect, a method for controlling an 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:
the method comprises the steps of considering the rotating speed of a low-pressure rotor of the aircraft engine and the area of a nozzle throat, constructing a control law of the area of the nozzle throat of the aircraft engine, transforming the rotating speed of the low-pressure rotor of the aircraft engine, and correcting 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 pressure ratio value, so that the consistency debugging of the thrust 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 this description, is intended to indicate that the subject matter preceding that word includes the elements listed thereafter, but not excluding others.
The present application will be described in further detail 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 low-pressure rotor rotating speed of the aircraft engine, and specifically constructing the aircraft engine nozzle throat area control law according to engineering experience, as shown in fig. 2, wherein A8 represents the aircraft engine nozzle throat area, and n1R represents the low-pressure rotor rotating speed of the 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, 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 modified 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 given by experience, and can also be determined by 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:
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, namely the thrust of the aircraft engine has 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 control law of the throat area of the jet pipe of the aircraft engine 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 jet pipe of the aircraft engine is further corrected, and correction is carried out within the range of the working point of the fan of the aircraft engine so as to control the surge margin of the aircraft engine and ensure the working stability of the fan of the aircraft engine.
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 the 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 order to ensure the effect of debugging the thrust consistency of the aircraft engine in the method for debugging the thrust consistency of the aircraft engine, before debugging, design correction is performed on other parameters that affect the thrust of the aircraft engine, such as the area of a high-pressure turbine guider, the area of a low-pressure turbine guider, and the angle control law of an inlet guide blade of a fan of the aircraft engine, as shown in fig. 4, where A1 represents the angle of the inlet guide blade of the fan of the aircraft engine.
In another aspect, a method for controlling an 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 invention 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 invention is not limited to those specific embodiments, and that equivalent changes or substitutions of the related technical features may be made by those skilled in the art without departing from the principle of the present invention, and those technical aspects after such changes or substitutions will fall within the scope of the present invention.
Claims (4)
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 commissioning 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 working point of the fan of the aircraft engine is characterized by W1R/pif;
wherein the content of the first and second substances,
W1R is the aircraft engine air flow;
pif is the aircraft engine fan pressure ratio.
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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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| CN114233512A CN114233512A (en) | 2022-03-25 |
| CN114233512B true CN114233512B (en) | 2023-03-14 |
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001075604A (en) * | 1999-09-06 | 2001-03-23 | Ishikawajima Harima Heavy Ind Co Ltd | Multivariable control method |
| US6269627B1 (en) * | 1998-12-16 | 2001-08-07 | United Technologies Corporation | Rapid thrust response control logic for shaft-driven lift fan STOVL engine |
| WO2006014189A2 (en) * | 2004-03-17 | 2006-02-09 | Decjet Incorporated | Axial flow pump and marine propulsion device |
| RU2451278C1 (en) * | 2011-03-16 | 2012-05-20 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Turbojet engine and method of its testing |
| JP2018059491A (en) * | 2016-10-03 | 2018-04-12 | 根本 勇 | Flow control method of ultrahigh bypass ratio variable cycle turbofan |
| CN108170965A (en) * | 2018-01-03 | 2018-06-15 | 中国航发沈阳发动机研究所 | A kind of design method for verifying variable cycle engine component overall performance scheme |
| RU2736403C1 (en) * | 2020-05-19 | 2020-11-16 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Turbojet engine control method |
| CN112761742A (en) * | 2021-01-27 | 2021-05-07 | 中国航发沈阳发动机研究所 | Dynamic stress measurement test debugging method for low-pressure turbine rotor blade of engine |
| CN113236441A (en) * | 2021-04-28 | 2021-08-10 | 中国科学院工程热物理研究所 | Turbine shaft-fan dual-mode engine and adjusting method thereof |
| CN113550839A (en) * | 2021-08-11 | 2021-10-26 | 南京航空航天大学 | Thrust vector turbofan engine model and vector deflection stabilization control device |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008063153A2 (en) * | 2006-10-12 | 2008-05-29 | United Technologies Corporation | Managing low pressure turbine maximum speed in a turbofan engine |
| US20110004388A1 (en) * | 2009-07-01 | 2011-01-06 | United Technologies Corporation | Turbofan temperature control with variable area nozzle |
| CN108894882B (en) * | 2018-06-05 | 2019-09-06 | 中国航发沈阳发动机研究所 | Aircraft engine size throttle thrust limits regular acquisition methods |
| GB201811861D0 (en) * | 2018-07-20 | 2018-09-05 | Rolls Royce Plc | Supersonic aircraft turbofan engine |
-
2021
- 2021-12-24 CN CN202111597789.XA patent/CN114233512B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6269627B1 (en) * | 1998-12-16 | 2001-08-07 | United Technologies Corporation | Rapid thrust response control logic for shaft-driven lift fan STOVL engine |
| JP2001075604A (en) * | 1999-09-06 | 2001-03-23 | Ishikawajima Harima Heavy Ind Co Ltd | Multivariable control method |
| WO2006014189A2 (en) * | 2004-03-17 | 2006-02-09 | Decjet Incorporated | Axial flow pump and marine propulsion device |
| RU2451278C1 (en) * | 2011-03-16 | 2012-05-20 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Turbojet engine and method of its testing |
| JP2018059491A (en) * | 2016-10-03 | 2018-04-12 | 根本 勇 | Flow control method of ultrahigh bypass ratio variable cycle turbofan |
| CN108170965A (en) * | 2018-01-03 | 2018-06-15 | 中国航发沈阳发动机研究所 | A kind of design method for verifying variable cycle engine component overall performance scheme |
| RU2736403C1 (en) * | 2020-05-19 | 2020-11-16 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Turbojet engine control method |
| CN112761742A (en) * | 2021-01-27 | 2021-05-07 | 中国航发沈阳发动机研究所 | Dynamic stress measurement test debugging method for low-pressure turbine rotor blade of engine |
| CN113236441A (en) * | 2021-04-28 | 2021-08-10 | 中国科学院工程热物理研究所 | Turbine shaft-fan dual-mode engine and adjusting method thereof |
| CN113550839A (en) * | 2021-08-11 | 2021-10-26 | 南京航空航天大学 | Thrust vector turbofan engine model and vector deflection stabilization control device |
Non-Patent Citations (2)
| Title |
|---|
| 喷管喉道面积变化对大涵道比分排涡扇发动机性能的影响;唐宇峰等;《航空发动机》;20110215(第01期);全文 * |
| 基于安装性能的航空发动机中间状态喷管调节计划优化;谢业平等;《航空动力学报》;20131220(第01期);全文 * |
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