基于超声速冲动式转子的下游静叶气动设计方法研究

Study of Aerodynamic Design Method for Downstream Stator Based on Supersonic Impulse Rotors

关键词:  超声速  轴流压气机  冲动式转子  数值模拟  气动设计 

Key words:  Supersonic  Axial compressors  Impulse rotors  Numerical simulation  Aerodynamic design

摘要:

针对超声速轴流压气机,分析了两类传统超声速压气机转子的内部流动特点。为有效解决超声速冲动式转子出口绝对马赫数过高,下游静叶设计困难的问题,提出了两种该类转子的下游静叶气动设计方法,并利用该方法对一冲动式转子进行了静叶匹配。基于数值模拟手段,对匹配结果进行了验证分析。三维粘性的数值模拟结果表明,该设计初步实现了最初设想的流动状态。其中,对于第一种静叶气动设计方法,在实现超声速入口来流降为亚声速但气流在静叶中折转可以忽略的情况下,实现了一级压比不低于2.2、级效率不小于82%的超声速压气机级设计；对于第二种静叶气动设计方法,实现了一级压比不低于2.1、级效率不小于77%的超声速压气机级设计。对于上述两种静叶设计方法,考虑到静叶入口存在正激波时级效率最高,因此该设计方法并没有达到有效降低静叶入口激波损失的目的。 

Abstract:

For supersonic compressors, the aerodynamic design characteristics of the two types of traditional supersonic rotors were analyzed. Taking into account the high exit absolute Mach number of the impulse rotors, which always may cause problems for the downstream stator design, two kinds of stator aerodynamic design methods were put forward. And stator was matched for a special impulse rotor with these two kinds of design methods separately. From the three-dimensional viscous numerical simulation results, the flow details have been initially realized.As for the first stator aerodynamic design method, the flow at the stator entrance is decreased to subsonic and the turning of the flow in the stator can even be ignored.A supersonic compressor stage has been attained with pressure ratio not less than 2.2and efficiency higher than 82%.As for the second stator aerodynamic design method, a compressor stage with pressure ratio not less than 2.1and efficiency higher than 77% has been attained. But considering the highest stage efficiency attained when a normal shock exits at the entrance of the stator, the design does not achieve the goals to reduce the shock losses by this method.