对涡旋流对跨声速压气机转子Rotor67的影响  

Effects of Paired Swirl Distortion on Rotor67 Transonic Compressor

作　　者：冯路宁 程邦勤[1] 王加乐 FENG Lu-Ning;CHENG Bang-Qin;WANG Jia-Le(Aeronautics Engineering College,Air Force Engineering University,Xi’an 710038,China)

机构地区：[1]空军工程大学航空工程学院,西安710038

出　　处：《工程热物理学报》2021年第9期2284-2291,共8页Journal of Engineering Thermophysics

摘　　要：为研究对涡旋流畸变对压气机的影响,本文基于一种新设计的旋流畸变发生器,利用CFD技术,开展了对涡旋流畸变与NASA Rotor67跨声速转子的数值仿真研究。在100%换算转速下,对比分析均匀进气以及旋流进气条件下的压气机压比、效率特性线以及流场分布情况。结果表明,对涡旋流会引起压气机增压能力和效率的下降,并降低压气机稳定工作裕度。在100%换算转速、旋流进气条件下压气机峰值效率点处的流量值较之均匀进气条件下降低2.33%,峰值效率降低2.44%,该点处压比降低0.25%。压气机失速点流量增加0.99%,压气机稳定工作流量范围下降。To research the effects of paired swirl distortion on compressor,based on a new type of swirl distortion generator and using the CFD technology,a numerical simulation study was carried out based on a paired swirl distortion generator and Rotor67 transonic compressor.With 100%corrected speed,the compressor pressure ratio,efficiency and flow field with uniform inflow are compared with the compressor pressure ratio,efficiency and flow field with paired swirl inflow.The results show that the paired swirl will decrease the pressure ratio and efficiency of the compressor,and reduce the stability margin of the compressor.With 100%corrected speed,the stability mass flow rate,the efficiency and pressure ratio of the compressor is reduced by 2.33%,2.44%and 0.25%in the peak efficiency point with the effects of paired swirl.The mass flow rate at the compressor stall point increases by 0.99%,and the stability margin of the compressor decreases.

关 键 词：CFD 对涡 Rotor67 旋流畸变 压气机 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]