Rapid diagnosis method for rotating stall of axial flow compressor based on determined learning theory
A technology for determining learning theory and axial flow compressors, applied in biological models, electrical digital data processing, special data processing applications, etc., and can solve problems such as difficulty in satisfying continuous excitation conditions
Patent Information
- Authority / Receiving Office
- CN · China
- Current Assignee / Owner
- Publication Date
- 2010-11-17
- Estimated Expiration
- Not applicable · inactive patent
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Abstract
Description
[0001] technology neighborhood
[0002] The invention relates to a rapid diagnosis method for the rotational stall of an axial flow compressor, in particular to a rapid diagnosis method for the rotational stall of an axial flow compressor based on deterministic learning theory. Background technique
[0003] Axial flow compressor plays an important role in turbomachinery and is one of the core components of turbofan engine and turbojet engine. The rotating stall of the axial flow compressor will not only significantly reduce the performance of the engine, but also cause the engine's turbine and combustion chamber to overheat and damage the turbine blades and other disastrous consequences, such as when the aircraft is in certain flight conditions (climbing and large maneuvering flight, etc.) The occurrence of rotating stall can easily cause serious accidents; rotating stall may also cause compressor surge (rotating stall is generally regarded as the precursor of surge). Therefo...
Examples
Embodiment
[0048] The schematic diagram of the overall structure of the aviation turbofan engine is shown in Figure (1). The air enters the compressor from the front air inlet of the engine through the guide vane cascade (wherein P T Indicates the external atmospheric pressure), the compressor pressurizes the low-pressure gas in the combustion chamber and burns it with fuel (such as gasoline) to form high-temperature and high-pressure gas, and the high-temperature and high-pressure gas is ejected from the tail nozzle to form a rebound force to provide the required power for the aircraft. Consider the following Mansoux model (finite-dimensional high-order dynamical system) for the rotating stall of the axial flow compressor:
[0049] E φ · = - Aφ + Ψ c ...