A method for identifying flameout in the main combustion chamber of a twin-rotor gas turbine engine
A gas turbine and main combustion chamber technology, applied in the field of aero-engine state detection, can solve problems affecting mission execution, endangering aircraft safety, long thrust recovery time, etc., and achieve the effect of improving safety
Active Publication Date: 2021-07-09
AECC SHENYANG ENGINE RES INST
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Problems solved by technology
The above process has the following disadvantages: 1) air parking will cause greater pressure to the pilot, the pilot also needs to pay attention to the parameter changes in the starting process and intervene when necessary, which increases the pilot's burden and affects the pilot's attention; 2) the engine thrust degrades greatly , the thrust recovery time is long, which will affect the mission execution; 3) If the air start fails, there will be an air parking failure, endangering the safety of the aircraft, and in severe cases, it will cause aircraft crash and death
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[0023] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...
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The application belongs to the technical field of aero-engine state detection, and in particular relates to a method for identifying flameout of a main combustion chamber of a dual-rotor gas turbine engine. The method includes determining the high-pressure rotor speed change rate when the engine is turned off at different low-pressure speeds or high-pressure speeds; Relationship Judgment When the real-time high-pressure rotor conversion speed change rate is greater than the real-time low-pressure conversion speed or the high-pressure rotor conversion speed corresponding to the real-time high-pressure conversion speed at the same moment, it is determined that the main combustion chamber is off, and the main combustion chamber of the engine of the present application is off. The method can effectively detect the flameout problem of the main combustion chamber, can effectively improve the safety of flight, and improve the combat effectiveness of the aircraft.
Description
technical field [0001] The application belongs to the technical field of aero-engine state detection, and in particular relates to a method for identifying flameout of a main combustion chamber of a twin-rotor gas turbine engine. Background technique [0002] When the gas turbine engine is working, the fuel is burned in the combustion chamber components, and the contained chemical energy is converted into heat energy, which is converted into power or thrust output through the impeller machinery. The aeroengine can also provide air for aircraft environmental control at the same time. If the main combustion chamber is turned off, the gas turbine engine will stop working and lose its function, which will seriously affect the safety of related equipment and personnel. When early gas engines were controlled by mechanical hydraulic systems, they did not have the conditions to use complex algorithms to detect and deal with them. After the engine adopts a digital control system, it...
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IPC IPC(8): G01M15/14G01M15/02
CPCG01M15/02G01M15/14
Inventor 袁继来姜繁生杨龙龙何孟虎张志舒
Owner AECC SHENYANG ENGINE RES INST