压气机动叶抽吸气的数值模拟探索

Numerical simulation research of aspiration on a compressor rotor blade

为了研究吸附式压气机,改善压气机性能,开展了在压气机动叶上采取主动流动控制措施对压气机性能影响的研究。采用计算流体力学(CFD)数值模拟方法,通过大量计算选择合适的吸气位置和吸气量,在动叶吸力面上开吸气孔进行附面层吸除,可以在一定程度上改善流动状况,从而对转子的效率、压比以及喘振裕度产生有利的影响。通过对NASA Rotor37实例计算表明,吸气后附面层分离状况得到明显改善,采用较小的吸气孔面积和吸气量就能对转子的效率、压比和喘振裕度产生正效应。不同的吸气位置,存在对应的最佳的吸气量。计算表明,转子最佳吸气位置在附面层的过渡区(包括附面层厚度的极大值位置)。

The research of active flow control＇s influence on compressor＇s performance has been developed for improving the compressor ＇s performance and studying the aspirated compressor. The efficiency, pressure ratio and stall margin of a rotor can be affected profitably as a result of the improving of flow state, by means of Boundary Layer Suction at rotor blade ＇s suction surface. The appropriate bleeding mass flow and location are selected after a lot of trial calculations using Computational Fluid Dynamics numerical simulation method, Calculations of Rotor37 show that the separated status of boundary layer has been observably improved, and that the positive impacts on rotor＇s performance have been achieved even with small bleeding mass flow and area. There must be the optimal bleeding mass flow corresponding to a bleeding location, The calculations show that the optimal bleeding location corresponding to a rotor must be in the transition region（including the location where the thickness of boundary layer is max）.