Super/transonic compressor with front sharp and blunt trailing edge bodies and design method thereof

Abstract

The invention discloses a super / transonic compressor with front sharp and blunt trailing edge bodies and a design method of the super / transonic compressor, and belongs to the technical field of aero-engine compressors. The super / transonic compressor is characterized in that the multiple sharp and blunt trailing edge bodies with certain height, length and width are evenly distributed on an outer machine case of an inlet of the compressor in the circumferential direction. The super / transonic compressor can be directly used as a high-performance aviation gas turbine engine compressor. On the premise that the layout and the pneumatic performance of an existing compressor are not changed, the stable working margin of the compressor is substantially improved. According to the super / transonic compressor, due to the fact that the front sharp and blunt trailing edge bodies are reasonably designed, the super / transonic compressor not only can work normally under the condition that only one gas inlet angle exists, but also can work normally under the condition that a certain positive attack angle or a certain negative attack angle is formed between the gas inlet direction and the front edge of an attracting force face, and the stable working margin of the compressor is improved on the premise that the efficiency of a fan or the compressor is not changed basically.

Description

technical field [0001] The invention relates to a super / transonic compressor with a front sharp and blunt trailing edge body on an imported outer casing and a design method thereof, which can greatly improve the super / transonic speed on the premise that the structural layout and efficiency of the compressor are basically unchanged. The stable working margin of the transonic compressor is especially suitable for high-performance aviation gas turbine engines. Background technique [0002] The compressor is one of the core components of the aero-engine and one of the most difficult to design. Increasing the single-stage pressure ratio of the compressor and reducing the structural weight are effective ways to increase the thrust-weight / power-to-weight ratio of the aero-engine. Continuously increasing the tangential speed of the compressor is an important trend in the development of the compressor, which can increase the single-stage pressure ratio of the compressor while keeping...

AI Technical Summary

Problems solved by technology

However, the sweeping three-dimensional shape of the blade will not only affect the strength and vibration characteristics of the compressor, but also increase the processing difficulty and manufacturing cost of the compressor blade.

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