Method and device for judging rotational stall of aviation gas turbine engine

An aviation gas turbine and rotating stall technology, which is applied in gas turbine devices, engine components, machines/engines, etc., can solve the problem of inability to judge the rotating stall, reduce the cost of model development, wide adaptability, and improve aerodynamic stability and reliability. sexual effect

Active Publication Date: 2021-12-28
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 rotational stall of aviation gas turbine engine
  • Method and device for judging rotational stall of aviation gas turbine engine
  • Method and device for judging rotational stall of aviation 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

This application belongs to the technical field of aero-engine control, and specifically relates to a method and device for judging a rotational stall of an aero-gas turbine engine, including: obtaining whether the engine is in a stopped state; If the high-pressure conversion speed is greater than the first set value, the static pressure at the compressor outlet is obtained, and the rate of change of the static pressure at the compressor outlet is calculated; if the rate of change of the static pressure at the compressor outlet is greater than the second set value, it is determined whether the engine is In the restart state; if the engine is in the non-restart state, then obtain the fan inlet static pressure; calculate the ratio of the compressor outlet static pressure to the fan inlet static pressure, if the ratio is less than the third set value , it is determined that the engine is in a rotational stall state. The application solves the technical problem that the rotating stall cannot be judged during the working process of the engine, reduces the risk of surge, and improves the aerodynamic stability and reliability of the engine.

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...

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Application Information

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Patent Type & Authority Patents(China)
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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