吸附式亚声速压气机叶栅气动性能实验及分析

基金项目: 国家自然科学基金(50676095)

Experimental investigations of aerodynamics performance of aspirate subsonic compressor cascade

1.
Institute of Engineering Thermophysics, Chinese Academy of Science, Beijing 100080, China
2.
Graduate School, Chinese Academy of Sciences, Beijing 100080, China

摘要: 以亚声速平面叶栅风洞为实验平台,在不同来流马赫数、攻角和吸气量状态下,测试吸附式压气机叶栅吸力面、压力面表面压力分布和叶栅尾缘等参数.结果表明,附面层吸除能促进附面层减薄,减少分离损失,有助于降低叶栅总压损失,提高气流折转能力,改善叶栅气动性能.合适吸气槽位置和吸气量的选择,有利于叶栅内部流动更趋合理.
- 航空、航天推进系统 /
- 附面层 /
- 内部流动 /
- 吸气量 /
- 吸气位置 /
- 压气机叶栅
Abstract: Based on the experimental platform-subsonic cascade wind tunnel,the parameters such as cascade suction surface,static pressure distribution on the surface of the cascade and cascade tail,were tested under different Mach numbers,incidence angles and suction flow rates.The results show that,the boundary layer suction could reduce the cascade's total pressure losses,decrease the deviation angles and improve the aerodynamics performance of cascade.With the appropriate suction slot location and suction flow rate,the internal flow of cascade will become more rational.
- aerospace propulsion system /
- boundary layer /
- internal flow /
- suction flow rate /
- suction slot location /
- compressor cascade

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