轴向间隙对对转压气机失速性能的影响  

Effects of Axial Gap on Stall Characteristics of Contra-Rotating Compressor

作　　者：高丽敏[1,2] 李瑞宇[1,2] 李晓军[3] 蔡宇桐 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]先进航空发动机协同创新中心,陕西西安710072 [3]中国燃气涡轮研究院,四川成都610500

出　　处：《推进技术》2015年第12期1802-1808,共7页Journal of Propulsion Technology

摘　　要：采用数值模拟的方法,通过对5种不同轴向间隙下多工况对转压气机性能及失速工况下流场结构的分析,研究了高转速对转压气机内转子轴向间隙大小对其失速性能的影响,并对近失速工况下产生性能变化的原因展开讨论。动/动交界面参数传递采用了冻结转子法,保证了小轴向间隙下数值模拟的准确性。研究表明:(1)随着轴向间隙的减小,对转压气机性能降低但稳定工作范围增大,设计轴向间隙40%C为基准(C为转子2,叶片根部轴向弦长转子2),20%C轴向间隙下对转压气机峰值效率较设计间隙下降低了2.2%,稳定裕度增加了59.5%;(2)轴向间隙的改变对下游转子进口畸变产生影响,进而影响整机气动性能;(3)下游转子进口畸变对叶根区域流场产生影响,使得效率、压力等气动性能下降,然而,进口畸变对叶顶间隙内流场的影响作用却可以扩大整机稳定工作范围。A numerical investigation about the effects of axial gap on the aerodynamic performance at stall inception of a high- speed contra- rotating axial flow compressor is reported, and the causes of performance change near stall condition are analyzed. The computation is carried out under several operating conditions with five different axial gap sizes. Full Non Matching Frozen Rotor method is used in rotor/rotor interface to ensure the accuracy of numerical simulation even with small axial clearance. The study shows that：（1） With the decreasing of the axial clearance size,the performance shows a downward trend,while the stable operation range is expended. Compared with the design axial gap（40%C）,the peak efficiency is reduced by 2.2%,while the operation range is expended by 59.5% with small axial gap（20%C）.（2） It is the main reason for the aerodynamic performance change in the compressor that the inlet distortion of downstream rotor varies with different axial gaps.（3）The flow field structure near the hub in the downstream rotor is influenced by the inlet distortion,which leads to the decrease of efficiency and pressure ratio. However,the stable operation range is expended due to the inlet distortion effects on the flow field in the tip gap.

关 键 词：对转压气机 轴向间隙 失速 进口畸变 

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]