某型航空发动机高压涡轮叶顶间隙三维数值分析

岂兴明; 朴英; 祝剑虹; 周建兴

某型航空发动机高压涡轮叶顶间隙三维数值分析

清华大学航空航天学院, 北京100084

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出版历程
- 收稿日期: 2007-05-23
- 修回日期: 2007-10-09
- 刊出日期: 2008-05-28

3-D numerical analysis of the tip clearance of an aero-engine high pressure turbine

School of Aerospace, Tsinghua University, Beijing 100084, China

摘要

摘要: 利用有限元分析软件计算出了某型航空发动机高压涡轮叶顶间隙的时间历程变化.分析过程中考虑了温度、压力和转速的影响,并给出了施加边界条件的新方法.通过与前人的计算方法进行对比分析,得出了较为合理的结果:转速的影响是轮盘径向尺寸变化的主要因素,而温度是影响机匣和叶片的主要因素,叶顶间隙分别在慢车突然加速和反推力状态下出现最小值.
- 航空、航天推进系统 /
- 叶顶间隙 /
- 有限元法 /
- 高压涡轮 /
- 数值分析
Abstract: By means of finite element method,the changes of the tip clearance of an aeroengine's high pressure turbine(HPT) were calculated,the influences of pressure,temperature and rotation speed were considered and a new method of applying the boundary conditions was presented as well.After comparison with and analysis of former methods,this paper has reached some reasonable conclusions: the shaft speed plays a major role in the displacement of turbine disc,while the temperature is a major influential factor to the blade and shroud.Minimum tip clearance will occur during the first acceleration of the engine and the re-burst processes,respectively.
- aerospace propulsion system /
- tip clearance /
- finite element method /
- high pressure turbine(HPT) /
- numerical analysis

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参考文献(15)

[1]	Lattime S,Steinetz B.Turbine engine clearance control systems:current practices and future directions[R].AIAA 2002-3790.
[2]	Halila E,Lenahan D,Thomas T.Energy efficient,high pressure turbine test hardware detailed design report[R].NASA CR-167955,1982.
[3]	Kawecki E J.Thermal response turbine shroud study[R].Air Force Aero Propulsion Laboratory Technical Report AFAPL-TR-79-2087,1979.
[4]	Wiseman M W,Guo T.An investigation of life extending control techniques for gas turbine engines[C]//Proceedings of the American Control Conference.Arlington,VA:2001.
[5]	Kim Y,Metzger D.Heat transfer and effectiveness on film cooled turbine blade tip models[J].ASME Journal of Turbomachinery,1995,117:12-21.
[6]	Kumada M,Iwata S,Obata M,et al.Tip clearance effect on heat transfer and leakage flows on the shroud-wall surface in an axial flow turbine[J].ASME Journal of Turbomachinery,1994,116:39-45.
[7]	Lattime S,Steinetz B,Robbie M.Test rig for evaluating active turbine blade tip clearance control concepts[R].AIAA-2003-4700,2003.
[8]	唐庆如.高压涡轮间隙控制[J].航空发动机,1997,(3):21-22.TAN Qinru.The tip clearance control of high pressure turbine[J].Aero-Engine,1997,(3):21-22.
[9]	漆文凯,陈伟.某型航空发动机高压涡轮叶尖间隙数值分析[J].南京航空航天大学学报,2003,35(1):63-67.QI Wenkai,CHEN Wei.Tip clearance numerical analysis of an aero-engine HPT[J].Journal of Nanjing University of Aeronautics & Astronautics,2003,35(1):63-67.
[10]	牛东生,陈伟,漆文凯.涡轮叶尖间隙计算实现方法与结果分析[J].燃气涡轮试验与研究,2004,17(4):31-34.NIU Dongsheng,CHEN Wei,QI Wenkai.Calculation program for turbine tip clearance and result analysis[J].Gas Turbine Experiment and Research,2004,17(4):31-34.
[11]	郭淑芬,徐波.温度与转速对涡轮叶尖径向间隙的影响[J].推进技术,2004,21(4):51-53.GUO Shufen,XU Bo.Effect of temperature and rotational speed on radial clearance of turbine blade tip[J].Journal of Propulsion Technology,2004,21(4):51-53.
[12]	王宝官.传热学[M].北京:航空工业出版社,1993.WANG Baoguan.Heat transfer[M].Beijing:Aviation Industry Press,1993.
[13]	Norhrop A,Owen J M.Heat transfer measurements in rotating-disc systems[J].International Journal of Heat and Fluid Flow,1988,9(1):19-26.
[14]	徐国强,丁水汀,陶智,等.中心进气旋转盘的冷却效果实验研究.热能动力工程,2000,87(15):260-263.XU Guoqiang,DING Shuiting,TAO Zhi,et al.A study on averaged heat transfer characteristic of a rotating cavity with axial fringe inflow[J].Journal of Aerospace Power,1998,113(13):260-263.
[15]	丁水汀,张东,陶智,徐国强.航空发动机高压旋转涡轮盘腔流动与换热[J].推进技术,2003,24(2):118-121.DING Shuiting,ZHANG Dong,TAO Zhi,et al.Numerical simulation for flow and heat transfer of a rotating turbine cavity with realistic engine parameters[J].Journal of Propulsion Technologv,2003,24(2):118-121.