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[15] 王栋 .脉冲爆震发动机工作过程数值模拟研究[D].南京:南京理工大学, 2007.* 收稿日期: 2017-07-07；修订日期: 2017-09-05。基金项目:国家自然科学基金( 91541109；51406234)；陕西省自然科学基金( 2015JQ5124)。通讯作者:赵坤,男,硕士生,研究领域为脉冲爆震发动机。 E-mail: 13228035006@163.com (编辑:史亚红)机匣温度边界条件对跨声转子性能的影响 *葛健 1,柳阳威 1,2,陆利蓬 1,2(1.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国家级重点实验室,北京 100191； 2.先进航空发动机协同创新中心,北京 100191)摘要:为探究机匣壁面温度对跨声转子性能的影响,利用数值模拟对等温机匣壁面和绝热机匣壁面两种情况的跨声转子 Rotor 37进行研究,对比分析了其对特性线、总温等参数的展向分布和叶顶流场结构的影响及其机理。结果表明,等温壁面相比于绝热壁面更接近实验的真实情况,采用等温壁面边界条件预测的出口总温径向分布在 90%叶高以上更符合实验数据。等温壁面边界条件使 Rotor 37转子的效率在数值上提升了约 2%,更接近实验数据,但对三维流场的进一步分析表明,其对转子真实性能的影响很小。通过对熵的对比分析发现,由于采用等温壁面,机匣和外界的热交换可达轮缘功的 1.4%,导致传统的绝热效率计算公式失效,而在使用增加了热交换项的修正效率公式后,两种温度边界条件的 Rotor 37重新计算的效率几乎相等。关键词:机匣；温度边界条件；效率；熵；跨声转子中图分类号:V231.3文献标识码:A文章编号:1001-4055(2018) 07-1486-08 DOI:10.13675/j.cnki.tjjs.2018.07.006 Effectsof Casing Temperature Boundary Condition on Performanceofa Transonic Rotor GE Jian1,LIU Yang-wei1,2,LU Li-peng1,2(1.National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beihang University,Beijing 100191,China； 2.Collaborative Innovation Center of Advanced Aero-Engine,Beijing 100191,China) Abstract:In order to investigate the influence of casing temperature on the performace of transonic rotors, numerical simulation of Rotor 37 was performed with two different temperature boundary conditions at casing, adiabatic end wall and isothermal end wall.A comprehensive comparison was studied in characteristic lines, spanwise distributions of properties like total temperature at the outlet and flow structures near the casing.It indi.cates that compared with the adiabatic casing,the isothermal casing is more according with the experimental con.dition,and the spanwise distribution of total temperature at the outlet is closer to experiment data above 90%span.Although the efficiency of the cases with isothermal end wall are 2% higher than those with adiabatic endwall,it shows the temperature has little influence on the performance of Rotor 37 through the flow-field analysis.According to the contrast of entropy,it is found the conventional adiabatic efficiency formula has failed in the iso.thermal end wall condition because the heat transfer between the surrounding and the casing is up to 1.4%,which is non-negligible.And the efficiency of the two casing are found to be almost equal using a corrected formulawhich added the heat transfer effect.Keywords:Casing；Temperature boundary condition；Efficiency；Entropy；Transonic rotor 参考文献:[1] Denton J D.Some Limitations of Turbomachinery CFD[R].AMSE GT 2010-22540.[2] Dunham J.CFD Validation for Propulsion System Com.ponents[R].France: Advisory Group for Aerospace Re.search and Development Neuilly-sur-seine,1998.[3] Denton J D.Lessons from Rotor 37[J].Journal of Ther.mal Science,1997,6(1): 1-13.[4] Bruna D,Turner M G.Isothermal Boundary Conditionat Casing Applied to the Rotor 37 Transonic Axial FlowCompressor[J].Journal of Turbomachinery,2013,135(3).[5]鞠鹏飞,宁方飞 .跨声压气机近失速流动特征的数值模拟研究[ J].推进技术, 2016,37(6): 1055-1064.(JU Peng -fei,NING Fang -fei.Numerical Study of Near -Stall Flow Feature on Transonic Compressor[J].Journal of Propulsion Technology,2016,37(6): 1055-1064.)[6] Coull J D,Atkins N R.The Influence of Boundary Con.ditions on Tip Leakage Flow[J].Journal of Turboma.chinery,2015,137(6).[7] Bruna D,Turner M G.A Rothalpy Analysis for the Iso.thermal Boundary Condition at Casing Applied to the Ro.tor 37 Transonic Axial Flow Compressor[C].San Anto.nio: ASME Turbo Expo 2013: Turbine Technical Confer.ence and Exposition,2013.[8] Reid L,Moore R D.Design and Overall Performance of Four Highly Loaded,High Speed Inlet Stages for an Ad.vanced High -Pressure-Ratio Core Compressor[R].NASA-TP-1337,1978.[9] Suder K L,Celestina M L.Experimental and Computa.tional Investigation of the Tip Clearance Flow in a Tran.sonic Axial Compressor Rotor[C].Houston: ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition,1994.[10] Suder K L.Experimental Investigation of the Flow Fieldin a Transonic,Axial Flow Compressor with Respect tothe Development of Blockage and Loss[R].NASA-TM-107310,1996.[11]段真真,柳阳威,陆利蓬 .周向槽机匣处理对某跨声转子性能影响的数值研究[ J].航空学报, 2014,35(8): 2163-2173.[12]谢喆,柳阳威,刘小华,等 .旋转进口畸变频率对跨声速压气机稳定性影响的数值研究[ J].航空发动机, 2015,41(5): 1-7.[13] Xie Z,Liu YW,Liu XH,et al.Effect of RANS Method on Stall Inception Eigenvalue Approach[R].ASME GT 2017-64708.[14] Sjolander S A,Cao D.Measurements of the Flow in an Idealized Turbine Tip Gap[J].Journal of Turbomachin.ery,1994,117(4).[15]刘波,茅晓晨,张鹏,等 .叶尖间隙效应对跨声速压气机性能影响的研究[ J].推进技术, 2016,37(8): 1401-1410.(LIU Bo,MAO Xiao-chen,ZHANG Peng,et al.[J].Journal of Propulsion Technology, 2016,37(8): 1401-1410.)
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[21] 张琦,刘程远,滕金芳,等 .间冷回热涡扇发动机热力学研究[ J].推进技术, 2017,38(3): 504-509.(ZHANG Qi,LIU Cheng-yuan,TENG Jin-fang,et al.Parametric Thermal Analysis of Intercooled and Recu.perated Turbofan Engine[J].Journal of Propulsion Technology,2017,38(3): 504-509.)* 收稿日期: 2017-07-10；修订日期: 2017-08-28。基金项目:国家自然科学基金项目( 51676007；51420105008；51790513)。作者简介:葛健,男,硕士生,研究领域为风扇激波噪声控制研究。 E-mail: gejiangj@126.com通讯作者:柳阳威,男,博士,副教授,研究领域为压气机内复杂流动预测及控制方法研究。 E-mail: liuyangwei@126.com (编辑:史亚红)
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