跨声速涡轮中两种叶片叶尖泄漏流的气动性能

钟芳盼; 周超; 周凯

跨声速涡轮中两种叶片叶尖泄漏流的气动性能

北京大学工学院航空航天工程系, 北京 100871

基金项目: 航空科学基金(2011ZB71002);国家自然科学基金(11202008)

计量
- 文章访问数: 1259
- HTML浏览量: 0
- PDF量: 1042
- 被引次数: 0
出版历程
- 收稿日期: 2012-10-26
- 刊出日期: 2013-10-28

Aerodynamic performance of tip leakage flow of two different blade tips in transonic turbine

Department of Aeronautics and Astronautics, College of Engineering, Peking University, Beijing 100871, China

摘要

摘要: 采用数值模拟的方法,研究了跨声速涡轮叶栅中平面叶尖和双肋叶尖泄漏流的气动性能.平面叶尖比双肋叶尖的叶尖间隙内马赫数高,有反射激波结构;双肋叶尖的叶尖间隙内马赫数较低,没有形成明显的反射激波结构.平面叶尖和双肋叶尖的叶尖泄漏流质量流量分别为叶栅进口质量流量的3.87%和3.74%.平面叶尖的气动损失系数为0.079,双肋叶尖的气动损失系数为0.072.研究表明,双肋叶尖的气动性能要好于平面叶尖.
- 跨声速 /
- 气动性能 /
- 高压涡轮 /
- 叶尖泄漏流 /
- 双肋叶尖 /
- 平面叶尖
Abstract: The aerodynamic performance of the tip leakage flow of flat tip and cavity tip was investigated numerically in transonic turbine cascade. The Mach number within the tip gap of flat tip was higher than that of cavity tip. Oblique shock wave structure appeared within the tip gap of flat tip. For cavity tip, the oblique shock wave structure was not obvious because of low Mach number within the tip gap. The mass flow ratios of tip leakage flow to the mass flow at the inlet of the cascade for flap tip and cavity tip were 3.87% and 3.74%, respectively. The aerodynamic loss coefficient was 0.079 for flat tip and 0.072 for cavity tip. The study shows that the aerodynamic performance of cavity tip is better than that of flat tip.
- transonic /
- aerodynamic performance /
- high pressure turbine /
- tip leakage flow /
- cavity tip /
- flat tip

HTML

参考文献(15)

[1]	邵卫卫,季路成,程荣辉,等.叶尖泄漏掺混损失影响因素分析[J].航空动力学报,2007,22(10):1722-1729. SHAO Weiwei,JI Lucheng,CHENG Ronghui,et al.Analysisof influential factors to tip leakage mixing loss[J].Journal of Aerospace Power,2007,22(10):1722-1729.(in Chinese)
[2]	Hassanvand M,WANG Songtao,FENG Guotai,et al.Calculation of the energy loss for tip leakage flow in turbines[J].Chinese Journal of Aeronautics:English Version,2004,17(3):142-148.
[3]	李伟,乔渭阳,许开富,等.涡轮叶尖间隙泄漏流动主动控制数值模拟[J].航空动力学报,2008,23(7):1260-1265. LI Wei,QIAO Weiyang,XU Kaifu,et al.Numerical simulation of active control on tip leakage flow in axial turbine[J].Journal of Aerospace Power,2008,23(7):1260-1265.(in Chinese)
[4]	曹传军,黄国平,夏晨.逆向涡流发生器减小涡轮叶尖泄漏流的数值研究[J].南京航空航天大学学报,2010,42(5):588-59. CAO Chuanjun,HUANG Guoping,XIA Chen.Numerical study in reducing tip leakage flow of turbine using backward vortex generators[J].Journal of Nanjing University of Aeronautics and Astronautics,2010,42(5):588-59.(in Chinese)
[5]	岂兴明,朴英,周建兴,等.涡轮叶顶间隙形态的优化[J].吉林大学学报:工学版,2009,39(4):874-879. QI Xingming,PIAO Ying,ZHOU Jianxing,et al.Optimization design of turbine blade tip clearance shapes[J].Journal of Jilin University:Engineering and Technology Edition,2009,39(4):874-879.(in Chinese)
[6]	冯涛,周颖,邹正平,等.向心涡轮内部流动数值模拟分析[J].航空动力学报,2006,21(3):448-454. FENG Tao,ZHOU Ying,ZOU Zhengping,et al.Numerical simulation of the flow inside radial inflow turbine[J].Journal of Aerospace Power,2006,21(3):448-454.(in Chinese)
[7]	Booth T C,Dodge P R,Hepwrth H K.Rotor tip leakage:Part I basic methodology[R].ASME Paper 81-GT-71,1981.
[8]	Ameri A A,Steinthorsson E,Rigby D L.Effect of squealer tip on rotor heat transfer and efficiency[J].Journal of Turbomachinery,1998,120(4):753-759.
[9]	Camci C,Dey D,Kavurmacioglu L.Tip leakage flows near partial squealer rims in an axial flow turbine stage[R].ASME Paper GT2003-38979,2003.
[10]	ZHOU Chao,Hodson H.The tip leakage flow of an unshrouded high pressure turbine blade with tip cooling[J].Journal of Turbomachinery,2011,133(4):041028.1-041028.12.
[11]	Key N,Arts T.Comparison of turbine tip leakage flow for flat tip and squealer tip geometries at high-speed conditions [R].ASME Paper GT2004-53979,2006.
[12]	Heyes F J G,Hodson H P,Dailey G M.The effect of blade tip geometry on the tip leakage flow in axial turbine[J].Journal of Turbomachinery,1992,114(3):643-651.
[13]	ZHANG Qiang,O'Dowd D O,He L,et al.Overtip shock wave structure and its impact on turbine blade tip heat transfer[J].Journal of Turbomachinery,2011,133(4): 041001.1-041001.8.
[14]	Denton J D.Loss mechanisms in turbomachines [R].ASME Paper 93-GT-435,1993.
[15]	ZHOU Chao,Hodson H.Squealer geometry effects on aerothermal performance of tip leakage flow of cavity tips[J].Journal of Propulsion and Power,2012,28(3):556-567.