压气机进气畸变数值模拟技术研究

流体力学与飞行力学

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压气机进气畸变数值模拟技术研究

安玉戈, 刘火星

北京航空航天大学能源与动力工程学院航空发动机气动热力科技重点实验室, 北京 100191

收稿日期:2011-10-14 修回日期:2011-12-09 出版日期:2012-09-25 发布日期:2012-09-22
通讯作者: 刘火星 E-mail:liuhuoxing@buaa.edu.cn
基金资助:
国家自然科学基金(51106004)

Numerical Simulation of Compressor with Inlet Distortion

AN Yuge, LIU Huoxing

National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beihang University, Beijing 100191, China

Received:2011-10-14 Revised:2011-12-09 Online:2012-09-25 Published:2012-09-22

摘要/Abstract

摘要： 发展了一种针对进气畸变条件下的风扇/压气机进行性能预估和稳定性分析的计算方法。首先研究了将叶片作用力简化为体积力源项的建模方法,在此基础上开发出一套基于体积力的三维进气畸变数值模拟程序,使用该程序对NASA Rotor 35在均匀进气、进口存在稳态总压畸变及同时存在总压和总温畸变的流场进行了模拟分析。结果表明,该程序获得的压气机特性及参数分布与雷诺平均Navier-Stokes(RANS)计算吻合得很好,同时正确地模拟出了压气机转子与上游畸变来流的耦合作用及其对压气机性能和稳定工作裕度的影响。

关键词: 航空航天推进系统, 风扇/压气机, 进气畸变, 体积力模型, 稳定性

Abstract: A numerical tool is developed to evaluate the performance and stability of fan/compressor with inlet distortion. First, the modeling method to replace the blade row forces with distributed bulk body force source terms is investigated. Then a three-dimensional computational fluid dynamics (CFD) code is developed by adding the model into an Euler solver to simulate the fan/compressor flow field with inlet distortion. A NASA Rotor 35 flow field with clean inlet, inlet steady total pressure distortion and combined total pressure total temperature distortion are simulated respectively with the code. It demonstrates that the results obtained by the code of NASA Rotor 35 with clean inlet agree well with the solutions of Reynolds average Navier-Stokes (RANS). In the case with inlet distortion, this code can obtain the key feature of the interaction of the rotor and upstream flow field, and its influence on rotor performance and stall margin.

Key words: aerospace propulsion system, fan/compressor, inlet distortion, body force model, stability

中图分类号:

安玉戈, 刘火星. 压气机进气畸变数值模拟技术研究[J]. 航空学报, 2012, 33(9): 1624.

AN Yuge, LIU Huoxing. Numerical Simulation of Compressor with Inlet Distortion[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(9): 1624.

参考文献

[1] Fidalgo V J, Hall C A, Colin Y. A study of fan-distortion interaction within the NASA Rotor 67 transonic stage. ASME Paper, GT-2010-22914, 2010.
[2] Callahan G M, Stenning A H. Attenuation of inlet flow distortion upstream of axial flow compressors. Journal of Aircraft, 1971, 8(4): 227-233.
[3] Henderson R E, Horlock J H. An approximate analysis of the unsteady lift on airfoils in cascade. ASME Paper, GT-1972-5, 1972.
[4] Greitzer E M, Mazzawy R S. Flow field coupling between compression system components in asymmetric flow. ASME Journal of Engineering for Power, 1978, 100(1): 66-72.
[5] Longley J P, Greitzer E M. Inlet distortion effects in aircraft propulsion system integration. AGARD Lecture Series, 1992.
[6] Mazzawy R S. Multiple segment parallel compressor model for circumferential flow distortion. ASME Journal of Engineering for Power, 1977, 99(2): 288-296.
[7] Hawthorne W R. Non-axisymmetric flow through annular actuator disks: inlet distortion problem. ASME Journal of Engineering for Power, 1978, 100(4): 604-617.
[8] Yao J, Gorrell S D,Wadia A R. A time-accurate CFD analysis of inlet distortion induced swirl in multistage fans. AIAA-2007-5059, 2007.
[9] Gorrell S E, Yao J,Wadia A R. High fidelity URANS analysis of swirl generation and fan response to inlet distortion. AIAA-2008-4985, 2008.
[10] Gong Y F. A computational model for rotating stall and inlet distortions in multistage compressors. Cambrige: Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, 1998.
[11] Hale A, O’Brien W. A three-dimensional turbine engine analysis compressor code (TEACC) for steady-state inlet distortion. Journal of Turbo-machinery, 1997, 120(3): 422-430.
[12] Chima R V. A three dimensional unsteady CFD model of compressor stability. ASME Paper, GT-2006-90040, 2006.
[13] Zheng N. 3D unsteady numerical simulation of fan/compressor with inletdistortion. Journal of Aerospace Power, 2007, 22(1): 60-65. (in Chinese) 郑宁. 风扇进气畸变三维非定常模拟技术研究. 航空动力学报, 2007, 22(1): 60-65.
[14] Xu L. Assessing viscous body forces for unsteady calculations. ASME Paper, GT-2002-30359, 2002.
[15] Reid L, Moore R D. Performance of a single-stage axial-flow compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 1.82. NASA Technical Paper 1338, 1978.

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

压气机进气畸变数值模拟技术研究

Numerical Simulation of Compressor with Inlet Distortion

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