Single-stage axial-flow high-pressure compressor with asymmetric end walls

Abstract

The present disclosure provides a single-stage axial-flow high-pressure compressor comprising a hub having an asymmetric end wall obtained by sweeping a profile line built in a blade channel, the profile line being a non-axisymmetric curve, and constructed using trigonometric functions.

Description

technical field [0001] The present disclosure relates to a single-stage axial-flow high-pressure compressor. Background technique [0002] With the great development of aviation technology, researchers are also exploring the limits of the performance of engine components. As one of the core components of the engine, the design and optimization of the compressor is a topic that researchers continue to pay attention to. However, as the stage pressure ratio of the axial flow compressor increases, the compressor continues to develop in the direction of low aspect ratio and high load. Separation and clogging become more prominent, resulting in a decrease in compressor efficiency and, in severe cases, a rotational stall of the compressor. Therefore, taking appropriate measures to reduce flow separation and blockage in the compressor is an effective way to increase the load of the compressor. [0003] For the boundary layer in the end zone and flow separation and clogging, bette...

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Problems solved by technology

However, because there is still a transverse pressure gradient in the compressor channel, the channel vortex is prone to corner separation when it flows from the pressure surface of the blade to the suction surface, resulting in an increase in secondary flow loss

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