摘要
针对某型航空发动机压气机转子叶片尾缘出现的叶尖掉块问题,设计了两种叶片尾缘端削方案,并评估了两种端削方式对压气机级性能的影响,揭示了压气机的失速机理及端削对失速裕度的影响机理。结果表明,端削使压气机的压比裕度降低约0.5%,将压气机的流量裕度提升1%以上,整体上对压气机效率的影响较小;通过对流场的定量分析发现,压气机的失速由转子叶根附近叶片吸力面附面层的分离诱发;转子叶尖尾缘端削改变了整个叶高范围内流量的径向分布,并通过提高转子叶根附近的流量降低了附面层的分离程度,进而提升了压气机的流量裕度;采用叶片尾缘斜切的端削方式对压气机性能的影响更小,可以作为解决叶尖掉块的一种处理方法。
In order to solve the problem of blade tip rupture at the trailing edge of rotor blade for an aero-engine compressor,two kinds of cutting schemes at the blade trailing edge were designed.The effects of the two cutting methods on the performance of compressor stage were evaluated using numerical simulations.The stall mechanism of the compressor and the influence mechanism of the blade cutting on stall margin were analyzed.The results show that the blade cutting reduces the margin of pressure ratio of the compressor by approximately 0.5%,and increases margin of compressor flow by more than 1%.The blade cutting at the trailing edge has little effect on the efficiency of the compressor.It is found that the compressor stall is induced by the boundary layer separation at the suction surface of rotor blade near the hub by implementing quantitative analysis of the flow field.The blade tip cutting at rotor trailing edge changes radial distribution of flow in the entire blade height range,reduces the separation degree of the boundary layer on the suction surface by increasing the mass flow near the hub,and further increases flow margin of the compressor.In contrast,the beveling cutting method along the blade trailing edge has less influence on the compressor performance,which can be used as a treatment method to solve the problem of blade tip rupture.
作者
史国华
SHI Guohua(AECC Aviation Power Co.,Ltd.,Xi'an 710021,China)
出处
《流体机械》
CSCD
北大核心
2023年第5期70-76,共7页
Fluid Machinery
基金
国家自然科学基金项目(52076179)。
关键词
轴流压气机
叶尖掉块
叶尖尾缘端削
失速裕度
失速机理
axial compressor
blade tip rupture
blade tip cutting at the trailing edge
stall margin
stall mechanism
作者简介
史国华(1977),男,高级工程师,主要从事涡轮喷气发动机和涡轮风扇发动机的整体性能和可靠性的研究工作,通信地址:710021陕西省西安市中国航发动力股份有限公司科技委,E-mail:sgh_1132021@163.com。
