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Method and device for judging rotating stall of aero-gas turbine engine

A technology for aviation gas turbines and rotating stalls, which is applied to gas turbine devices, engine components, jet propulsion devices, etc., and can solve problems such as the inability to judge rotating stalls

Active Publication Date: 2020-01-31
AECC SHENYANG ENGINE RES INST
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Problems solved by technology

[0005] In order to solve at least one of the above technical problems, this application provides a method and device for judging the rotational stall of an aviation gas turbine engine, which aims to solve the technical problem that the rotational stall cannot be judged during the working process of the engine under the existing scheme, and reduce the occurrence of surge risk, improve the aerodynamic stability and reliability of the engine, and ensure flight safety

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  • Method and device for judging rotating stall of aero-gas turbine engine
  • Method and device for judging rotating stall of aero-gas turbine engine
  • Method and device for judging rotating stall of aero-gas turbine engine

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Embodiment Construction

[0036] 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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Abstract

The invention belongs to the technical field of aero-engine control, and particularly relates to a method and device for judging rotating stall of an aero-gas turbine engine. The method comprises thesteps that whether the engine is in a stopped state or not is obtained; if the engine is in a non-stopped state, the high-pressure conversion rotating speed of the engine is obtained; if the high-pressure conversion rotating speed is larger than a first set value, the outlet static pressure of a gas compressor is obtained, and the change rate of the outlet static pressure of the gas compressor iscalculated; if the change rate of the outlet static pressure of the gas compressor is larger than a second set value, whether the engine is in a restarted state or not is determined; if the engine isin a non-restarted state, the inlet static pressure of a fan is obtained; and the ratio of the outlet static pressure of the gas compressor to the inlet static pressure of the fan is calculated, and if the ratio is smaller than a third set value, that the engine is in a rotating stall state is determined. According to the method and device, the technical problem that the rotating stall cannot be judged in the working process of the engine is solved, the risk of surge is reduced, and the aerodynamic stability and reliability of the engine are improved.

Description

technical field [0001] The application belongs to the technical field of aero-engine control, and in particular relates to a method and device for judging a rotational stall of an aero-gas turbine engine. Background technique [0002] The unstable operation types of aero-engine compressors can be divided into two types: rotating stall and surge. The rotating stall is the precursor of the surge, and the surge is the result of the extreme development of the rotating stall. When surge occurs, parameters such as the flow rate and outlet pressure of the compressor will oscillate at low frequency and high amplitude over time, and in severe cases, backflow will occur. This may lead to reduced engine performance, increased turbine thermal load and vibration stress, and even damage to the structural integrity of the engine, directly threatening flight safety. [0003] At present, several types of aviation gas turbine engines under research in China use surge pressure differential si...

Claims

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Application Information

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IPC IPC(8): F01D21/00F01D21/14F02C9/00
CPCF01D21/003F01D21/14F02C9/00
Inventor 杨龙龙好毕斯嘎拉图姜繁生邴连喜张志舒陈泽华
Owner AECC SHENYANG ENGINE RES INST
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