不同范围进口畸变对亚声轴流压气机的影响

张皓光; 安康; 谭锋; 楚武利; 吴艳辉

doi:10.13224/j.cnki.jasp.2018.04.002

不同范围进口畸变对亚声轴流压气机的影响

doi: 10.13224/j.cnki.jasp.2018.04.002

1.
西北工业大学动力与能源学院，西安 710072
2.
西北工业大学动力与能源学院，西安 710072；先进航空发动机协同创新中心，北京 100191

基金项目: 国家自然科学基金重点项目（51536006）；国家自然科学基金（51006084）；航空科学基金（2014ZB53014）；陕西省自然科学基金（2015JM5202）

计量
- 文章访问数: 814
- HTML浏览量: 5
- PDF量: 972
- 被引次数: 0
出版历程
- 收稿日期: 2016-10-17
- 刊出日期: 2018-04-28

Influence of inlet distortion of different ranges on subsonic axial-flow compressor

摘要

摘要: 借助于计算流体动力学商用软件NUMECA，通过使用10通道非定常数值模拟的方法，研究了不同范围的进口气流畸变对亚声速轴流压气机性能、稳定性和流场的影响。研究对象是西北工业大学单级轴流亚声压气机转子。不同范围的进口畸变是通过在进口径向段设置不同范围栏杆的方法产生的。结果表明：进口畸变不但降低了压气机转子的性能，而且使转子的稳定工作范围减少。畸变范围越大，上述现象越明显。通过详细分析内部流场表明：畸变后，由于部分通道叶顶间隙泄漏流溢流和附面层分离的影响，造成通道内严重的堵塞，进而诱发转子失速。畸变范围越大，影响也越大。
- 不同范围 /
- 进口畸变 /
- 轴流压气机 /
- 非定常 /
- 栏杆
Abstract: By means of computational fluid dynamics commercial software NUMECA, the effects of inlet distortion of different range on the performance, stability and flow-field in a subsonic axial-flow compressor were investigated with ten-annulus unsteady numerical method. The research object was the single-stage subsonic axial-flow compressor rotor of Northwestern Polytechnical University. The inlet distortion of different range was generated by setting some barriers on the inlet ring surface. Results showed that inlet distortion didnt only degrade the performance of the compressor rotor, but also decreased the stability of the rotor. And the larger distortion range indicated the more obvious phenomenon mentioned above. The fundamental flow mechanism was obtained by detailed analysis of the flow-field in rotor passage. Inlet distortion led to serious blockage in tip blade passage and further induced rotor stall because of the influence of the tip clearance leakage flow and the separation of boundary layer in some tip blade suction. Like above, the larger distortion range meant the more serious influence.
- different ranges /
- inlet distortion /
- axial-flow compressor /
- unsteady /
- barrier

HTML

参考文献(15)

[1]	WALKER C L,SIVO J N,JANSEN E T.Effects of unequal air-flow distribution from twin inlet ducts on performance of an axial-flow turbojet engine［R］.NACA RM E54E13,1954.
[2]	HARRY D P,LUBICK R J.Inlet-air distortion effects on stall,surge and acceleration margin of a turbo-jet engine equipped with variable compressor inlet guide vanes［R］.NACA RM E54K26,1955.
[3]	LUEDKE J G.Use of nonlinear Volterra theory in predicting the propagation of non-uniform flow through an axial compressor［D］.Blacksburg,Virginia:Virginia Polytechnic Institute and State University,2001.
[4]	WALLACE R M.Modal response of a transonic fan blade to periodic inlet pressure distortion［D］.Blacksburg,Virginia:Virginia Polytechnic Instituted State University,2003.
[5]	HALE A,OBRIEN W.A three-dimensional turbine engine analysis compressor code (TEACC) for steady-state inlet distortion［J］.Journal of Turbomachinery,1998,120(3):422-430.
[6]	GONG Y,TAN C S,GORDON G S,et al.A computational model for short wavelength stall inception and development in multistage compressors［R］.Journal of Turbomachinery,1999,121(3):726-734.
[7]	郑宁,邹正平,徐立平.风扇进气畸变三维非定常数值模拟技术研究［J］.航空动力学报,2007,22(1):60-65．ZHENG Ning,ZOU Zhengping,XU Liping.3-D unsteady numerical simulation of fan/compressor with inlet distortion［J］.Journal of Aerospace Power,2007,22(1):60-65.(in Chinese)
[8]	尹超,胡骏,郭晋,等.进气畸变对压气机性能影响的三维彻体力模型［J］.航空动力学报,2015,30(9):2241-2250.YIN Chao,HU Jun,GUO Jin,et al.Three-dimensional body-force model for effect on compressor performance of inlet distortion［J］.Journal of Aerospace Power,2015,30(9):2241-2250.(in Chinese)
[9]	HIRAI K,KODAMA H,NOZAKI O,et al.Unsteady three-dimensional analysis of inlet distortion in turbomachinery［R］.AIAA 97-2735,1997.
[10]	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,2009,27(1):12-16.ZHANG Yanfeng,CHU Wuli,LU Xingen.Numerical simulation of the effect of total pressure inlet distortion on a subsonic axial-flow compressor［J］.Journal of Northwestern Polytechnical University,2009,27(1):12-16.(in Chinese)
[11]	陈美宁,朴英,王大磊.总压进气畸变对压气机转子气动影响的数值模拟［J］.航空动力学报,2009,24(8):1792-1798.CHEN Meining,PIAO Ying,WANG Dalei.Numerical simulation of the effect of total pressure inlet distortion on a compressor rotor［J］.Journal of Aerospace Power,2009,24(8):1792-1798.(in Chinese)
[12]	LESSER A,ISELER J,NIEHUIS R.Numerical investigation of a highly loaded axial compressor stage with inlet distortions［R］.ASME Paper GT2011-46457,2011.
[13]	孙鹏,高海洋,都昆,等.两种形式总压畸变对超声速压气机流场影响的数值研究［J］.工程热物理学报,2013,34(5):830-835.SUN Peng,GAO Haiyang,DU Kun,et al.Numerical study of a supersonic compressor with two forms of inlet total pressure distortion［J］.Journal of Engineering Thermophysics,2013,34(5):830-835.(in Chinese)
[14]	KHALEGHI H,JALALY R.Effects of circumferential inlet distortion on the performance of a transonic fan together with the impact of tip injection［R］.ASME Paper 2016-GT-58145,2016.
[15]	张皓光.轴流压气机机匣处理的试验与数值研究［D］.西安:西北工业大学,2008.ZHANG Haoguang.Experimental and numerical investigation of casing treatment on an axial-flow compressor［D］.Xian:Northwestern Polytechnical University,2008.(in Chinese)