叶顶间隙对高压涡轮动叶应力影响的数值研究

李钰洁; 刘永葆

doi:10.13224/j.cnki.jasp.2014.07.024

叶顶间隙对高压涡轮动叶应力影响的数值研究

doi: 10.13224/j.cnki.jasp.2014.07.024

海军工程大学动力工程学院, 武汉 430033

基金项目:

预研基金（4010303010303）

详细信息

作者简介:
李钰洁（1987-），男，山东滨州人，博士生，主要研究方向为舰船动力及热力系统的监测。

中图分类号: V231.3
计量
- 文章访问数: 1408
- HTML浏览量: 1
- PDF量: 986
- 被引次数: 0
出版历程
- 收稿日期: 2013-04-11
- 刊出日期: 2014-07-28

Numerical investigation of effect of tip clearance on stress of high pressure turbine rotor

College of Power Engineering, Naval University of Engineering, Wuhan 430033, China

摘要

摘要: 针对叶顶间隙直接影响高压涡轮动叶气动特性及结构可靠性的问题，对不同叶顶间隙下的涡轮动叶进行了气热耦合数值计算.通过对流体域与固体域在物理边界上能量的传递进行耦合计算，揭示了泄漏涡流运动对叶片所受温度、压力分布的影响规律，分析了叶片热应力、气动力变化对结构强度的影响.结果表明：随着叶顶间隙高度的增加，泄漏流速增加，热应力变化明显，叶顶间隙高度在0.3%~3.0%变化过程中，叶片最大等效应力增大2.6%.所得结果可为叶顶间隙控制提供理论依据.
- 叶顶间隙 /
- 气热耦合 /
- 泄漏流 /
- 涡轮动叶 /
- 热应力
Abstract: For the problem that tip clearance of the high pressure turbine rotors has a significant effect on the aerodynamic characteristic and structural reliability, numerical simulation based on conjugate heat transfer method of turbine rotors with different tip clearance sizes was performed. Coupled caculation of the energy transferred from physical interface between fluid and solid was made. The effects of leadage vortex flow on the distribution of temperature and pressure were presented, and the effects of thermal stress and aerodynamic stress on the structure intensity of blades were analyzed. It showed that, with the increase of tip clearance height, the leakage flow velocity increased and the thermal stress changed significantly. The maximum equivalent stress increased by 2.6% increase while the tip clearance height changed from 0.3% to 3.0%. The acquired results can provide a theoretical basis for tip clearance control.
- tip clearance /
- conjugate heat transfer /
- leakage flow /
- turbine rotor /
- thermal stress

HTML

参考文献(21)

[1]	Seong E L,Sang W L,Ho S K.Tip leakage aerodynamics over stepped squealer tips in a turbine cascade[J].Experiment Thermal and Fluid Science,2011,35(1):135-145.
[2]	Bunker R S.A review of turbine blade tip heat transfer[J].Annals of the New York Academy of Sciences,2001,934(1):64-79.
[3]	Metzger D E,Dunn M G,Hah C.Turbine tip and shroud heat transfer[J].Journal of Turbomachinery,1991,113(1):502-507.
[4]	Teng S Y.Gas turbine blade film cooling and blade tip heat transfer .Texas,US:The Texas University,2000.
[5]	XIAO Xinwen.Investigation of tip clearance flow physics in axial flow turbine rotors .Philadelphia,Pennsylvania,US:The Pennsylvania State University,2000.
[6]	Mazur Z,Hernandez-Rossette A,Garcia-Illescas R,et al.Analysis of conjugate heat transfer of a gas turbine first stage nozzle[R].ASME Paper GT2005-68004,2005.
[7]	Both D,Heuer T.Conjugate flow and heat transfer calculation of a high pressure turbine nozzle guide vane[R].AIAA-2001-3304,2001.
[8]	邢景棠,周盛,崔尔杰.流固耦合力学概述[J].力学进展,1997,27(1):19-30. XING Jingtang,ZHOU Sheng,CUI Erjie.Fluid-structure coupling mechanics summarization[J].Advances in Mechanics,1997,27(1):19-30.(in Chinese)
[9]	郭军刚,胡丽国,王春侠.流固耦合在涡轮叶片瞬态传热仿真中的应用[J].机械科学与技术,2010,29(4):455-460. GUO Jungang,HU Liguo,WANG Chunxia.Application of liquid-solid coupled numerical simulation method in transient heat transfer calculation of turbo-blade[J].Mechanical Science and Technology for Aerospace Engineering,2010,29(4):455-460.(in Chinese)
[10]	陶海亮,朱阳历,郭宝亭.压气机叶片流固耦合数值计算[J].航空动力学报,2012,27(5):1054-1059. TAO Hailiang,ZHU Yangli,GUO Baoting.Numerical simulation of aeroelastic response in compressor based on fluid-structure coupling[J].Journal of Aerospace Power,2012,27(5):1054-1059.(in Chinese)
[11]	岂兴明,朴英,矫津毅.高压涡轮叶顶间隙变化的数值分析[J].吉林大学学报:工学版,2009,39(1):33-37. QI Xingming,PIAO Ying,JIAO Jinyi.Numerical analysis of high pressure turbine tip clearance variation[J].Journal of Jilin University:Engineering and Technology Edition,2009,39(1):33-37.(in Chinese)
[12]	张小伟,王延荣,张潇.涡轮机械叶片的流固耦合数值计算方法[J].航空动力学报,2009,24(7):1622-1626. ZHANG Xiaowei,WANG Yanrong,ZHANG Xiao.Numerical method for fluid-structure interaction in turbomachinery bladings[J].Journal of Aerospace Power,2009,24(7):1622-1626.(in Chinese)
[13]	李海滨,冯国泰,王松涛.涡轮三维叶栅的气热耦合数值模拟[J].工程热物理学报,2003,24(5):770-772. LI Haibin,FENG Guotai,WANG Songtao.Numerical simulation method of aerodynamics-thermodynamic coupling in 3-D turbine cascade[J].Journal of Engineering Thermophysics,2003,24(5):770-772.(in Chinese)
[14]	杨俊杰,王荣桥,樊江.涡轮叶片的气动-热-结构多学科设计优化研究[J].航空动力学报,2010,25(3):617-622. YANG Junjie,WANG Rongqiao,FAN Jiang.Multi-disciplinary aero-dynamic-thermal-structure design optimization for turbine blade[J].Journal of Aerospace Power,2010,25(3):617-622.(in Chinese)
[15]	王大磊,朴英,陈美宁.高压涡轮转子间隙泄漏流动的非定常特征研究[J].航空动力学报,2012,27(11):2569-2576. WANG Dalei,PIAO Ying,CHEN Meining.Study of unsteady tip leakage flow characteristic in high pressure turbine stage[J].Journal of Aerospace Power,2012,27(11):2569-2576.(in Chinese)
[16]	牛茂升,藏述升,黄名海.间隙高度对涡轮叶顶间隙流动的影响[J].工程热物理学报,2008,29(6):935-939. NIU Maosheng,ZANG Shusheng,HUANG Minghai.Effect of tip clearance height on tip clearance flow in turbine rotors[J].Journal of Engineering Thermophysics,2008,29(6):935-939.(in Chinese)
[17]	房友龙,刘永葆,余又红.热和离心力耦合作用下燃气涡轮叶顶间隙变化研究[J].海军工程大学学报,2011,23(3):22-25. FANG Youlong,LIU Yongbao,YU Youhong.Blade tip clearance of gas turbine under influence of centrifugal and heat[J].Journal of Naval University of Engineering,2011,23(3):22-25.(in Chinese)
[18]	董平.航空发动机气冷涡轮叶片的气热耦合数值模拟研究[D].哈尔滨:哈尔滨工业大学,2009. DONG Ping.Research on conjugate heat transfer simulation of aero turbine engine air-cooled vane[D].Harbin:Harbin Institute of Technology,2009.(in Chinese)
[19]	Menter F R.Two equation eddy viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
[20]	Menter F R.Zonal two-equation model k-ω models for aerodynamic flow[R].AIAA 93-2906,1993.
[21]	《中国航空材料手册》编辑委员会.中国航空材料手册[M].北京:中国标准出版社,2002.