进口畸变对轴流压气机流场影响的全通道数值研究

推进技术 ›› 2013, Vol. 34 ›› Issue (8): 1056-1063.

进口畸变对轴流压气机流场影响的全通道数值研究

张皓光,吴俊,楚武利,吴艳辉,王维

西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072

发布日期:2021-08-15
作者简介:张皓光(1981—),男,博士,副教授,研究领域为叶轮机械气动势力学。E-mail:zhg@nwpu.edu.cn
基金资助:
国家自然科学基金(51006084);国家自然科学基金重点项目(51236006)；陕西省自然科学基金(2011JQ7018)；西北工业大学基础研究基金(JC201116)。

Full-Annulus Numerical Investigation of Influence on Flow-Field in an Axial Flow Compressor with Inlet Distortion

School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China

Published:2021-08-15

摘要/Abstract

摘要： 采用全通道非定常数值模拟方法研究了进口畸变对亚声速轴流压气机性能及流场的影响,数值模拟中通过在进口径向段设置栏杆的方式产生畸变,非定常数值计算结果表明进口总压畸变后降低了压气机转子的性能,失速裕度减小了3.1%。通过详细地分析压气机进口延伸段及内部流场表明,畸变后在转子上游进口环面上出现低值进气角区,促使部分通道叶顶吸力面附面层分离起始位置靠前,造成通道内堵塞严重,并使叶顶间隙泄漏流在更高叶展前缘处溢流到相邻叶片通道进而诱发转子失速,进口均匀时压气机失速主要是由叶顶间隙泄漏流引起的堵塞造成。 

关键词: 进口畸变;轴流压气机;全通道;栏杆;进气角;气流分离 

Abstract: Effects of inlet distortion on the performance and flow-field of subsonic axial-flow compressor were investigated with full-annulus numerical method.The inlet distortion was made by setting some barriers in the inlet radial passage. The unsteady numerical calculative results show that inlet distortion decreases the performance of the compression rotor and reduces stall margin by 3.1%. The fundamental flow mechanism was obtained by detailed analyzing the flow-filed in inlet extended passage and in rotor passage. The underlying mechanism is that there are some regions of low value of inlet flow angle on the ring surface of rotor inlet upstream and those make the separated location of boundary in some tip blade suction move toward blade leading, which leads to serious blockage in tip blade passage. The blockage makes the tip clearance leakage flow spill to adjacent tip passage at leading edge on higher blade span, inducing rotor stall consequently. When the inlet flow-field of rotor is uniform, the blockage caused by tip clearance leakage flow is the primary cause resulting in rotor stall. 

Key words: Inlet distortion; Axial-flow compressor; Full-annulus; Barrier; Inlet flow angle; Flow separation

张皓光,吴俊,楚武利,吴艳辉,王维. 进口畸变对轴流压气机流场影响的全通道数值研究[J]. 推进技术, 2013, 34(8): 1056-1063.

ZHANG Hao-guang,WU Jun,CHU Wu-li,WU Yan-hui,WANG Wei. Full-Annulus Numerical Investigation of Influence on Flow-Field in an Axial Flow Compressor with Inlet Distortion[J]. Journal of Propulsion Technology, 2013, 34(8): 1056-1063.

参考文献

[1] Aerospace Information Report 1419Revision A.Inlet Total Pressure Distortion Considerations for Gas2Turbine Engines[R].Society of Automotive Engineers, 1999.
[2] Luedke J G.Use of Nonlinear Volterra Theory in Predicting the Propagation of Non-Uniform Flow Through an Axial Compressor[D].Blacksburg:Virginia Polytechnic Institute and State University, 2001.
[3] Wallace R M.Modal Response of a Transonic Fan Blade to Periodic Inlet Pressure Distortion[D].Blacksburg:Vir-ginia Polytechnic Institute and State University, 2003.
[4] 孙鹏, 冯国泰.稳态周向总压畸变对小型风扇影响的全周数值模拟[J].推进技术,2006,7(3):239-242.(SUN Peng, FENG Guo-tai.Numerical Simulation of Effects of Steady Circumferential Total Pressure Distortion on a Small Fan[J].Journal of Propulsion Technology, 2006,7(3):239-242.)
[5] 孙鹏, 冯国泰, 隗东伟.总压畸变对小型风扇气动影响的数值模拟[J].热能动力工程,2006,1(3):259-263.
[6] Hirai K, Kodama H, Nozaki O,et al.Unsteady Three-Dimensional Analysis of Inlet Distortion in Turbomachinery[R].AIAA 97-2735.
[7] 张燕峰,楚武利,卢新根.进口总压畸变对亚音速轴流压气机流场影响数值研究[J].西北工业大学学报,2009,7(1):12-16.
[8] Jerez Fidalgo1V,Hall C A,Colin Y.A Study of Fan-Distortion Interaction with in the NASA Rotor 67Transonic Stage[R].ASME 2010-GT-22914.
[9] Donald S Madden, Matt A West.Effects of Inlet Distortion on the Stability of an Advanced Military Swept Fan Stage with Casing Treatment[R].ASME 2005-GT-68693.
[10] Thomas Peters, Thomas Brgener, Leonhard Fottner.Effects of Rotating Inlet Distortion on a 5-Stage Hp-Compressor[R].ASME 2001-GT-0300.
[11] Thomas Peters, Leonhard Fottner.Effects of Co- and Counter-Rotating Inlet Distortions on a 5-Stage Hp-Compressor[R].ASME 2002-GT-30395.
[12] 张皓光,楚武利,吴艳辉,等.轴向倾斜缝机匣处理影响压气机性能的机理[J].推进技术,2010,31(5):555-561.(ZHANG Hao-guang,CHU Wu-li,WU Yan-hui,et al.Investigation of the Flow Mechanism of Affecting Compressor Performance with Axial Skewed Slots Casing Treatment[J].Journal of Propulsion Technology, 2009,31(5):555-561.)
[13] 张皓光,楚武利,吴艳辉,等.压气机端壁自适应流通延迟失速的数值分析[J].推进技术,2009,30(2):202-208.(ZHANG Hao-guang,,CHU Wu-li,WU Yan-hui,et al.Numerical Investigation of the Flow Mechanisms of Compressor Stall Delay Through end Wall Self Recirculation[J].Journal of Propulsion Technology,2009,30(2):202-208.)
[14] Huu Duc Vo,Choon S Tan, Edward M Greitzer.Criteria for Spike Initiated Rotating Stall[R].ASME 2005-GT-68374.
[15] 李清鹏,吴艳辉,楚武利,等.轴流压气机转子近失速工况全通道数值模拟[J].航空动力学报,2011,26(10):2330-2338.