鼓包前缘静叶在跨声速压气机中应用初探

Preliminary Investigation on Tubercle Leading Edge

关键词:  静叶  鼓包前缘  附面层分离  性能  数值模拟

Key words:  Stator blade  Tubercle leading edge  Boundary layer separation  Performance  Numerical simulation

摘要:

为减小静叶吸力面表面的流动分离，提高压气机气动性能，对跨声速压气机的静子叶片进行鼓包前缘造型，研究鼓包前缘设计参数的影响。数值模拟结果表明:鼓包前缘使静叶表面静压重新分布，改善了流场结构；鼓包波峰产生的对涡结构能够抑制静叶吸力面附面层分离，减小分离区范围；50%叶高以下范围提高效率和总压比较为显著，50%叶高以上范围效率和总压比反而略有降低；在不降低压气机气动稳定性的前提下，效率和总压比分别提升约2%和0.5%，表明鼓包前缘静叶可提高压气机气动性能。

Abstract:

In order to reduce flow separation region on suction surface of stator blades，and improve aerodynamic performance of the compressor，tubercle leading edge stator blades with different design variables were used in a transonic compressor. The numerical simulation results show that tubercle leading edge can redistribute the static pressure on blade surface and improve the structure of flow field. The crest of each tubercle will generate twin swirl which will suppress suction surface boundary layer separation and reduce separation region. The efficiency and total pressure ratio are significantly improved within the region below 50% span，and reduced slightly above 50% span. Efficiency and the total pressure ratio will increase 2% and 0.5%，respectively，without reducing aerodynamic stability of the compressor，which means that the tubercle leading edge stator blades can improve aerodynamic performance of compressor.