CN111997761A - Method and system for improving plateau starting success rate of aeroengine - Google Patents
Method and system for improving plateau starting success rate of aeroengine Download PDFInfo
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- CN111997761A CN111997761A CN202010861196.9A CN202010861196A CN111997761A CN 111997761 A CN111997761 A CN 111997761A CN 202010861196 A CN202010861196 A CN 202010861196A CN 111997761 A CN111997761 A CN 111997761A
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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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/27—Fluid drives
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Eletrric Generators (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
Abstract
The application provides a method for improving the plateau starting success rate of an aircraft engine, which belongs to the technical field of aircraft engine control and comprises the following steps: acquiring a plateau state signal, a wheel load signal, a high-pressure rotor rotating speed signal and an engine starting signal; judging whether the airplane is in a plateau state according to the plateau state signal, judging whether the airplane is in a ground state according to the wheel load signal, and judging whether an engine is in a starting state according to the high-pressure rotor rotating speed signal and the engine starting signal; and when the situation that the airplane is in the plateau state, the ground state and the engine is in the starting state are simultaneously met, unloading the hydraulic system corresponding to the engine on the current side. By the method, the success rate of starting the aircraft engine in the plateau environment can be improved.
Description
Technical Field
The application belongs to the technical field of aero-engine control, and particularly relates to a method and a system for improving the plateau starting success rate of an aero-engine.
Background
At present, the conventional aircraft in China generally has the requirement of high altitude take-off and landing, but the air in the plateau area is thin and the pressure of the air is low, so that the air flow is reduced when the engine is started, the output power is reduced, and the engine is difficult to start. With the exposure of the problems of large engine dispersion degree, high exhaust temperature, long starting time and the like when the airplane is started on the plateau in recent years, the starting performance of the airplane is seriously influenced.
Disclosure of Invention
The application aims to provide a method and a system for improving the plateau starting success rate of an aeroengine, so as to solve or reduce at least one problem in the background art.
On one hand, the technical scheme of the application is as follows: a method of increasing the success rate of a plateau start of an aircraft engine, the method comprising:
acquiring a plateau state signal, a wheel load signal, a high-pressure rotor rotating speed signal and an engine starting signal;
judging whether the airplane is in a plateau state according to the plateau state signal, judging whether the airplane is in a ground state according to the wheel load signal, and judging whether an engine is in a starting state according to the high-pressure rotor rotating speed signal and the engine starting signal;
and when the situation that the airplane is in the plateau state, the ground state and the engine is in the starting state are simultaneously met, unloading the hydraulic system corresponding to the engine on the current side.
In the method of the present application, determining whether the engine is in a start state by the high pressure rotor speed signal and the engine start signal includes:
judging whether the rotating speed of the high-pressure rotor of the engine is less than a preset rotating speed or not, and judging whether an engine starting signal is effective or not;
and if the rotating speed of the high-voltage rotor of the generator is less than the preset rotating speed and the starting signal of the engine is effective, judging that the engine is in a starting state.
According to the method, after the front-side engine is started successfully, the hydraulic system corresponding to the front-side engine is loaded.
In the method, after the engine on one side is successfully started and the corresponding hydraulic system is loaded, the engine on the other side repeats the steps to finish the starting of the engines on the two sides of the airplane.
In the method of the present application, the hydraulic systems on both sides are simultaneously disconnected after the engines on both sides have been successfully started.
On one hand, the technical scheme of the application is as follows: a system for increasing the success rate of altitude start of an aircraft engine, the system comprising:
the plateau state change-over switch is used for generating a plateau state signal;
the airplane wheel load sensor is used for generating a wheel load signal;
the rotating speed sensor is used for generating a high-pressure rotor rotating speed signal;
an engine start switch for generating an engine start signal;
the electromechanical integrated management system judges whether the airplane is in a plateau state according to the plateau state signal, judges whether the airplane is in a ground state according to the wheel load signal and judges whether an engine is in a starting state according to the high-pressure rotor rotating speed signal and the engine starting signal; when the situation that the airplane is in the plateau state, the ground state and the engine is in the starting state is judged to be met simultaneously, the hydraulic system corresponding to the engine on the current side is unloaded.
In the system of this application, judge whether the engine is in the starting condition through high pressure rotor rotational speed signal and engine start signal, include:
judging whether the rotating speed of the high-pressure rotor of the engine is less than a preset rotating speed or not, and judging whether an engine starting signal is effective or not;
and if the rotating speed of the high-voltage rotor of the generator is less than the preset rotating speed and the starting signal of the engine is effective, judging that the engine is in a starting state.
In the system, after the front-side engine is started successfully, the hydraulic system corresponding to the front-side engine is loaded.
In the system, after the engine on one side is successfully started and the corresponding hydraulic system is loaded, the engine on the other side repeats the steps to finish the starting of the engines on the two sides of the airplane.
The system of the application also comprises a hydraulic unloading switch which is used for disconnecting the hydraulic systems on the two sides simultaneously after the engines on the two sides are started successfully.
The invention designs a method for unloading a hydraulic system when an airplane is started in a plateau and reloading the hydraulic system after an engine is successfully started, and under the condition of not influencing the normal work of the hydraulic system, the method increases the residual power by reducing the extracted power in the starting process of the engine, thereby improving the success rate of the plateau starting of the engine.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of a method for improving the plateau start success rate of an aircraft engine according to the present application.
FIG. 2 is a schematic diagram of a system for improving the plateau start success rate of an aircraft engine according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
As shown in fig. 1, the method for improving the plateau start success rate of the aircraft engine provided by the application comprises the following steps:
s1, acquiring a plateau state signal, a wheel load signal, a high-pressure rotor rotating speed signal and an engine starting signal;
s2, judging whether the airplane is in a plateau state according to the plateau state signal, judging whether the airplane is in a ground state according to the wheel load signal, and judging whether the engine is in a starting state according to the high-pressure rotor rotating speed signal and the engine starting signal;
and S3, when the situation that the airplane is in the plateau state, the ground state and the engine is in the starting state is judged to be met simultaneously, unloading the hydraulic system corresponding to the engine on the current side.
In the method, the process of judging whether the engine is in a starting state or not through a high-pressure rotor rotating speed signal and an engine starting signal comprises the following steps:
s21, judging whether the rotating speed of the high-pressure rotor of the engine is less than a preset rotating speed or not, and judging whether an engine starting signal is effective or not;
and S22, if the rotating speed of the high-voltage rotor of the generator is less than the preset rotating speed and the starting signal of the engine is effective, the engine is judged to be in a starting state.
Further, after the engine on the current side is started successfully, the hydraulic system corresponding to the engine on the current side is loaded again.
And finally, after the engine on one side is successfully started and the corresponding hydraulic system is loaded, the engine on the other side repeats the steps to finish the starting of the engines on the two sides of the airplane.
In the present application, the hydraulic systems on both sides are disconnected simultaneously after the engines on both sides have been successfully started.
As shown in fig. 2, the system for improving the plateau start success rate of the aircraft engine provided by the present application includes:
a plateau state changeover switch 11 (also referred to as a "plateau/plain changeover switch") for generating a plateau state signal;
a wheel load sensor 12 for generating a wheel load signal;
a rotation speed sensor 131 for generating a high-pressure rotor rotation speed signal;
an engine start switch 132 for generating an engine start signal;
the electromechanical integrated management system 14 judges whether the airplane is in a plateau state according to the plateau state signal, judges whether the airplane is in a ground state according to the wheel load signal, and judges whether the engine is in a starting state according to the high-pressure rotor rotating speed signal and the engine starting signal; when the situation that the airplane is in the plateau state, the ground state and the engine is in the starting state is judged to be met simultaneously, the hydraulic system corresponding to the engine on the current side is unloaded.
In the system of this application, through high pressure rotor rotational speed signal and the process that engine start signal judged whether the engine is in the starting condition, include:
judging whether the rotating speed of the high-pressure rotor of the engine is less than a preset rotating speed or not, and judging whether an engine starting signal is effective or not;
and if the rotating speed of the high-voltage rotor of the generator is less than the preset rotating speed and the starting signal of the engine is effective, judging that the engine is in a starting state.
Further, after the front-side engine is started successfully, the hydraulic system corresponding to the front-side engine is loaded again.
And finally, after the engine on one side is successfully started and the corresponding hydraulic system is loaded, the engine on the other side repeats the steps to finish the starting of the engines on the two sides of the airplane.
The system is also provided with a hydraulic unloading switch for disconnecting the hydraulic systems on the two sides simultaneously after the engines on the two sides are started successfully.
The first embodiment is as follows: the process of starting the left engine of the airplane at plateau will be described by taking the example of the method and the system of the present application.
When the airplane is in a plateau, before starting the left engine, the plateau state change-over switch 11 is firstly set to the 'plateau' position to generate a high-pressure state signal, and the hydraulic unloading switch 15 is set to the 'on' position, so that the electromechanical integrated management system 14 can control the hydraulic pump of the hydraulic system. Then, the left engine is started, and the electromechanical integrated management system 14 comprehensively judges according to signals of the wheel load sensor 12, the rotation speed sensor 131, the engine start switch 132, and the like, under the following conditions:
a) the plateau state change-over switch 11 is located at the position of plateau;
b) the airplane wheel load sensor 12 detects that the airplane is in a loading state (unloading and loading are not allowed in the air);
c) the rotating speed sensor 131 detects that the rotating speed of the high-pressure rotor of the left engine is less than 15% of the normal rotating speed;
d) the left engine start signal is changed from inactive to active.
If the 4 conditions are met simultaneously, the electromechanical integrated management system 14 outputs a left engine hydraulic unloading instruction, and the left engine hydraulic unloading instruction is transmitted to the hydraulic pump 16 of the hydraulic system I through the hydraulic unloading switch 15, so that unloading control on the hydraulic system I is realized. After a certain time (30 seconds), if the rotating speed of the high-pressure rotor of the left engine is greater than 63% of the normal rotating speed, the left engine is considered to be started successfully after a certain time delay (30 seconds), and the electromechanical integrated management system 14 outputs a left engine hydraulic loading instruction to the hydraulic pump 16 of the hydraulic system I to load the hydraulic system I.
If the left engine hydraulic unloading instruction is output by the electromechanical integrated management system 14, and the rotating speed of the high-pressure rotor of the left engine is still less than 15% of the normal rotating speed after a certain time (30 seconds), the left engine is considered to be failed to start, and the left engine needs to be restarted.
Example two: the process of starting the right engine of the airplane at plateau is described as an example in combination with the method and the system of the present application.
When the airplane is in a plateau, before the right engine is started, the plateau state change-over switch 11 is firstly set to the plateau position to generate a plateau state signal, and the hydraulic unloading switch 15 is set to the switch-on position, so that the electromechanical integrated management system can control the hydraulic pump of the hydraulic system. Then, the right engine is started, the electromechanical integrated management system comprehensively judges according to signals of the wheel load sensor 12, the rotating speed sensor 131 and the engine starting switch 132, and the like, and the following conditions are judged:
a) the plateau state change-over switch 11 is located at the position of plateau;
b) the airplane wheel load sensor 12 detects that the airplane is in a loading state (unloading and loading are not allowed in the air);
c) the rotating speed sensor 131 detects that the rotating speed of the high-pressure rotor of the right engine is less than 15% of the normal rotating speed;
d) the right engine start signal is changed from inactive to active.
If the 4 conditions are met simultaneously, the electromechanical integrated management system 14 outputs a hydraulic unloading instruction of the right engine, and the hydraulic unloading instruction is transmitted to a hydraulic pump 16 of the II hydraulic system through a hydraulic unloading switch 15, so that unloading control of the II hydraulic system is realized. After a certain time (30 seconds), if the rotating speed of the high-pressure rotor of the right engine is greater than 63% of the normal rotating speed, the right engine is considered to be started successfully after a certain time (30 seconds) is delayed, and the electromechanical integrated management system 14 outputs a hydraulic loading instruction of the right engine to the hydraulic pump 17 of the II hydraulic system to load the II hydraulic system.
If the electromechanical integrated management system 14 outputs a right engine hydraulic unloading instruction, and the rotating speed of the high-pressure rotor of the right engine is still less than 15% of the normal rotating speed after a certain time (30 seconds), the right engine is considered to be failed to start, and the right engine needs to be restarted.
Example three: the following describes the prevention of false unloading after the left and right engines are successfully started by combining the method and the system of the application.
In order to prevent the I and II hydraulic systems 16/17 from being unloaded by mistake after the engine is started successfully, a single-blade hydraulic unloading switch 15 containing two groups of contacts is arranged in the application, and an I hydraulic system unloading control cable and an II hydraulic system unloading control cable at the output end of the electromechanical integrated management system 14 are respectively connected to the two groups of contacts of the switch. When the left engine and the right engine are started successfully, the switch is set to the 'off' position, so that the hydraulic systems I and II can be switched off simultaneously, the hydraulic systems I and II can not be unloaded by mistake, and the reliability of the system is improved.
The method and the system are characterized in that a plateau state change-over switch is arranged, when an airplane is started on a plateau, the switch is shifted to a plateau position to generate a plateau state signal, an electromechanical integrated management system collects the switch state and carries out integrated processing after combining the airplane wheel load state, the engine high-pressure rotor rotating speed and an engine starting signal, if a hydraulic unloading condition is met, the electromechanical integrated management system outputs unloading control signals to a hydraulic pump of a hydraulic system I and a hydraulic pump of a hydraulic system II respectively to unload the hydraulic system, and after the engine is started successfully, the electromechanical integrated management system outputs loading control signals to the hydraulic pump of the hydraulic system I and the hydraulic pump of the hydraulic system II respectively to load the hydraulic system; meanwhile, in order to prevent the electromechanical integrated management system from outputting an unloading control signal in the air by mistake, a hydraulic unloading switch is also arranged at the rear end of the output of the electromechanical integrated management system, the switch needs to be set to a switch-on position before the plateau is started, and the switch is set to a switch-off position after the engine is started successfully, so that the hydraulic system is prevented from being unloaded by mistake. The method improves the starting success rate of the engine by 47 percent through verification.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A method for improving the plateau start success rate of an aeroengine is characterized by comprising the following steps:
acquiring a plateau state signal, a wheel load signal, a high-pressure rotor rotating speed signal and an engine starting signal;
judging whether the airplane is in a plateau state according to the plateau state signal, judging whether the airplane is in a ground state according to the wheel load signal, and judging whether an engine is in a starting state according to the high-pressure rotor rotating speed signal and the engine starting signal;
and when the situation that the airplane is in the plateau state, the ground state and the engine is in the starting state are simultaneously met, unloading the hydraulic system corresponding to the engine on the current side.
2. The method for improving the plateau starting success rate of the aeroengine according to claim 1, wherein the step of judging whether the engine is in a starting state or not through the high-pressure rotor speed signal and the engine starting signal comprises the following steps:
judging whether the rotating speed of the high-pressure rotor of the engine is less than a preset rotating speed or not, and judging whether an engine starting signal is effective or not;
and if the rotating speed of the high-voltage rotor of the generator is less than the preset rotating speed and the starting signal of the engine is effective, judging that the engine is in a starting state.
3. The method for improving the plateau starting success rate of the aeroengine as claimed in claim 1, wherein after the starting of the engine at the front side is successful, a hydraulic system corresponding to the engine at the front side is loaded.
4. The method as claimed in claim 3, wherein after the engine on one side is successfully started and loaded with the corresponding hydraulic system, the engine on the other side repeats the above steps to complete the starting of the engines on both sides of the aircraft.
5. The method for improving the plateau start success rate of the aeroengine as claimed in claim 4, wherein the hydraulic systems on both sides are disconnected simultaneously after the engines on both sides are started successfully.
6. A system for increasing the success rate of altitude start of an aircraft engine, the system comprising:
the plateau state change-over switch is used for generating a plateau state signal;
the airplane wheel load sensor is used for generating a wheel load signal;
the rotating speed sensor is used for generating a high-pressure rotor rotating speed signal;
an engine start switch for generating an engine start signal;
the electromechanical integrated management system judges whether the airplane is in a plateau state according to the plateau state signal, judges whether the airplane is in a ground state according to the wheel load signal and judges whether an engine is in a starting state according to the high-pressure rotor rotating speed signal and the engine starting signal; when the situation that the airplane is in the plateau state, the ground state and the engine is in the starting state is judged to be met simultaneously, the hydraulic system corresponding to the engine on the current side is unloaded.
7. The method for improving the plateau starting success rate of the aeroengine according to claim 6, wherein the step of judging whether the engine is in a starting state or not through the high-pressure rotor speed signal and the engine starting signal comprises the following steps:
judging whether the rotating speed of the high-pressure rotor of the engine is less than a preset rotating speed or not, and judging whether an engine starting signal is effective or not;
and if the rotating speed of the high-voltage rotor of the generator is less than the preset rotating speed and the starting signal of the engine is effective, judging that the engine is in a starting state.
8. The method for improving the plateau starting success rate of the aeroengine as claimed in claim 6, wherein after the starting of the engine at the front side is successful, a hydraulic system corresponding to the engine at the front side is loaded.
9. The method as claimed in claim 8, wherein after the engine on one side is successfully started and loaded with the corresponding hydraulic system, the engine on the other side repeats the above steps to complete the starting of the engines on both sides of the aircraft.
10. A method of increasing the success rate of a plateau start of an aeroengine as claimed in claim 9 wherein the system further includes a hydraulic unloading switch for simultaneously disconnecting the hydraulic systems on both sides when both engines have been successfully started.
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| CN202010861196.9A CN111997761B (en) | 2020-08-25 | 2020-08-25 | Method and system for improving plateau starting success rate of aeroengine |
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| CN202010861196.9A CN111997761B (en) | 2020-08-25 | 2020-08-25 | Method and system for improving plateau starting success rate of aeroengine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112731958A (en) * | 2020-12-01 | 2021-04-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne wheel-borne signal using method based on speed protection |
| CN113323732A (en) * | 2021-06-01 | 2021-08-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for measuring turbine work in starting process of aeroengine with running |
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| CN110195656A (en) * | 2018-02-26 | 2019-09-03 | 波音公司 | Hybrid turbine jet engine and the method for operating it |
| CN111520234A (en) * | 2020-04-30 | 2020-08-11 | 中国直升机设计研究所 | Starting device and method for helicopter engine in plateau environment |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112731958A (en) * | 2020-12-01 | 2021-04-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne wheel-borne signal using method based on speed protection |
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| CN113323732A (en) * | 2021-06-01 | 2021-08-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for measuring turbine work in starting process of aeroengine with running |
| CN113323732B (en) * | 2021-06-01 | 2022-09-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for measuring turbine work in belt-running starting process of aeroengine |
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