不同叶尖间隙下的涡轮转子出口 三维流场测量

熊兵; 万钎君; 石小江; 陈洪敏; 马宏伟

不同叶尖间隙下的涡轮转子出口三维流场测量

1.
中国航空工业集团公司燃气涡轮研究院, 四川江油 621703
2.
南京航空航天大学能源与动力学院, 南京 210016
3.
北京航空航天大学能源与动力工程学院, 北京 100191

计量
- 文章访问数: 2093
- HTML浏览量: 351
- PDF量: 807
- 被引次数: 0
出版历程
- 收稿日期: 2011-12-15
- 刊出日期: 2012-05-28

Measurements of three-dimensional flow field at exit of a turbine rotor passage in different tip clearances

1.
Gas Turbine Establishment, Aviation Industry Corporation of China, Jiangyou Sichuan 621703, China
2.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
3.
School of Jet Propulsion, Beijing University of Aeronautis and Astronautics, Beijing 100191, China

摘要

摘要: 采用圆锥四孔高频压力探针测量了某涡轮不同叶尖间隙下转子出口的三维时均流场.结果表明转子出口参数均呈现明显的周期特性.叶尖间隙对转子出口流动品质有较大影响;间隙大时,泄漏流显著,对应的机匣二次流动较弱;间隙小时,机匣附近的二次流动较强.泄漏流区域的速度低,对应的相对总压小,损失大;泄漏流导致气流亏转,对应的静压高,膨胀程度小于主流,增大间隙,膨胀比变小,涡轮做功能力下降.
- 涡轮 /
- 转子出口 /
- 三维流动 /
- 叶尖间隙 /
- 泄漏流
Abstract: The time-resolved flow field downstream of a turbine rotor with different tip clearances was measured using a fast-response four-hole pressure probe.The results show that the flow is obviously periodic due to the rotor.It also indicates that the tip leakage flow has profound effects on the flow field.With bigger tip clearance,the leakage flow is relatively stronger and the secondary flow near the casing wall is weaker.When the tip gap is smaller,the secondary flow near the casing wall becomes stronger.The velocity in the leakage flow region is very low and the loss is high,which leads to substantial flow blockage.The flow under-turning due to the leakage flow is also clearly seen in the measurements.The static pressure in the leakage flow is higher than that in the main flow.The work done by the rotor with bigger tip clearance is lower than that with smaller tip clearance.
- turbine /
- the rotor outlet /
- 3-D(three-dimensional) flow /
- tip clearance /
- leakage flow

HTML

参考文献(13)

[1]	Hennecke D K,Trappmann K.Turbine tip clearance control in gas turbine engines.NASA N83-29254,1983.
[2]	Chaluvadi V S P,Kalfas A I,Hodson H P.Vortex transport and blade interactions in high pressure turbines.ASME GT 2003-38389,2003.
[3]	Schlienger J,Kalfas A I,Abhari R S.Vortex-wake-blade interaction in a shrouded axial turbine.ASME 2004-GT-53915,2004.
[4]	綦蕾.涡轮端区非定常相互作用机理及流动控制技术探讨.北京:北京航空航天大学,2004. QI Lei.Investigations of unsteady interaction mechanism and flow control in the turbine end-wall regions.Beijing:Beijing University of Aeronautics and Astronautics,2004.(in Chinese)
[5]	Mansour M,Chokani N,Kalfas A L,et al.Impact of time-resolved entropy measurement on a one-and-one-half-stage axial turbine performance.ASME Paper 2008-GT-50807,2008.
[6]	Yamamoto A.Producation and development of secondary flows and losses in two types of straight turbine cascades[J].Journal of Turbomachinery,1987,109(2):186-193.
[7]	Wang H P,Olson S J,Goldstein R J,et al.Folw visualization in a linear turbine cascade of high performance turbine blades[J].Journal of Turbomachinery,1997,119(1):1-8.
[8]	Trerml K M,Lawless P B.Particle image velocimetry of vane-rotor interaction in a turbine stage.AIAA-98-3599,1998.
[9]	Kind R J,Serjak P J,Abbott M W P,et al.Measurements and prediction of the effects of surface roughness on profile losses and deviation in a turbine cascade.ASME Paper 96-GT-203,1996.
[10]	Ristic D,Lakshminarayana B,Chu S.Three dimensional flow field downstream of an axial flow turbine rotor.AIAA-98-3572,1998.
[11]	Miller R J,Moss R W,Ainsworth R W,et al.The development of turbine exit flow in a swan-necked inter-stage diffuser.ASME 2003 GT-38174,2003:863-875.
[12]	綦蕾,邹正平,刘火星,等.高负荷涡轮端区非定常流动相互作用研究[J].航空学报,2009,30(4):584-596. QI Lei,ZOU Zhengping,LIU Huoxing,et al.Unsteady flow interaction in endwall regions of high-loaded turbine stage[J].Acta Aeronautics et Astronautics Sinica,2009,30(4):584-596.(in Chinese)
[13]	马宏伟,蒋浩康,董玉玺.单转子轴流压气机不同状态下进出口三维时均流场[J].航空动力学报,2000,15(2):119-123. MA Hongwei,JIANG Haokang,DONG Yuxi.Three-dimensional mean flow field at both inlet and exit of an isolated axial compressor rotor passage in different conditions[J].Journal of Aerospace Power,2000,15(2):119-123.(in Chinese)