动静干涉对涡轮转子叶片气膜冷却的影响

李虹杨; 郑赟

doi:10.13700/j.bh.1001-5965.2015.0054

动静干涉对涡轮转子叶片气膜冷却的影响

doi: 10.13700/j.bh.1001-5965.2015.0054

李虹杨^1,2,
郑赟^1,2, ,

1.
北京航空航天大学能源与动力工程学院, 北京 100083
2. 先进航空发动机协同创新中心, 北京 100083

详细信息

作者简介:
李虹杨男,博士研究生。主要研究方向:流、热耦合数值模拟,转捩预测及仿真。E-mail:buaalihy@hotmail.edu.cn;郑赟男,博士,讲师。主要研究方向:计算流体力学,叶轮机流、热、固耦合仿真,航空发动机叶片振动数值仿真。Tel.:010-82338753E-mail:zheng_yun@buaa.edu.cn

通讯作者:
郑赟,Tel.:010-82338753E-mail:zheng_yun@buaa.edu.cn

中图分类号: V211.6
计量
- 文章访问数: 1039
- HTML全文浏览量: 140
- PDF下载量: 480
- 被引次数: 0
出版历程
- 收稿日期: 2015-01-26
- 网络出版日期: 2016-01-20

Effect of rotor-stator interaction on film-cooling of turbine blade

LI Hongyang^1,2,
ZHENG Yun^{1,2
, ,}

1.
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100083, China

摘要

摘要: 为研究动静干涉对涡轮转子叶片气膜冷却效果的影响,选取AGTB涡轮叶栅作为研究对象,匹配前排导叶并对整级叶栅进行非定常数值模拟。对不同时刻流场截面的流动情况以及叶片表面温度随时间的演化规律进行了详细的分析,此外,总结了尾迹和势干涉对下游叶片气膜冷却的影响。主要结论如下:导叶强烈的势干涉作用在幅值为12°的范围内改变下游叶片的入射角,对冷却射流有非常大的影响;尾迹和势干涉作用诱导冷却射流的"上扬"现象,并使其冷气流量增加20%以上,有利于提高瞬时的冷却效果;势干涉对前缘冷却射流的作用时间约为1/2个静子周期,尾迹的作用时间约为1/6个静子周期,前者作用时间长,且效果更强。受到输运效果的影响,整个叶片冷却效果的变化与气膜孔射流状态的变化不是同步的,滞后时间可达1/3个静子周期甚至更长。
- 动静干涉 /
- 势干涉 /
- 尾迹 /
- 非定常 /
- 气膜冷却 /
- 涡轮
Abstract: For the purpose of studying the effect of rotor-stator interaction on film-cooling of turbine blade, the AGTB turbine cascade was chosen to do the research, with which a vane row was assembled. Unsteady numerical simulation was made for the full stage. The cross-section flow field at different instants of time and variation of temperature distribution of the blade over time were analyzed in detail. Furthermore, influence of wake and potential interference on film-cooling of downstream blade was discussed. Conclusions are as follows: the strong potential interference of the vane could change the flow angle of downstream blade in the range of 12°, which has a great influence on cooling jet; both the wake and potential interference could induce cooling jet "uptrend" and increase the mass flow of the cooling air by more than 20%, enhancing instant cooling performance; function time of potential interference was about 1/2 stator period, while that of the wake was about 1/6 stator period, and the potential interference usually performs longer time and has stronger effects than the wake. Affected by the transport effects, variations of cooling performance of the whole blade and flow condition of cooling jet were not synchronous, of which the latency time could be about 1/3 stator period or even longer.
- rotor-stator interaction /
- potential interference /
- wake /
- unsteady /
- film-cooling /
- turbine

HTML全文

参考文献(24)

[1]	DROST U,BOLCS A.Investigation of detailed film cooling effectiveness and heat transfer distributions on a gas turbine airfoil[J].Journal of Turbomachinery,1999,121(2):233-242.
[2]	SEN B,SCHMIDT D L,BOGARD D G.Film cooling with compound angle holes:Heat transfer[J].Journal of Turbomachinery,1996,118(4):800-806.
[3]	TENG S,HAN J C,POINSATTE P E.Effect of film-hole shape on turbine-blade heat-transfer coefficient distribution[J].Journal of Thermophysics and Heat Transfer,2001,15(3):249-256.
[4]	戴萍,林枫.气膜孔形状对涡轮叶片气膜冷却效果的影响[J].热能动力工程,2009,24(5):560-565. DAI P,LIN F.Influence of air-film hole shapes on turbine blade air-film cooling effectiveness[J].Journal of Engineering for Thermal Energy and Power,2009,24(5):560-565(in Chinese).
[5]	KIM S I,HASSAN I.Unsteady heat transfer analysis of a film cooling flow[C]//46th AIAA Aerospace Sciences Meeting and Exhibit.Reston:AIAA,2008:2008-1287.
[6]	OU S,HAN J C,MEHENDALE A B,et al.Unsteady wake over a linear turbine blade cascade with air and CO₂ film injection:Part I:Effect on heat transfer coefficients[J].Journal of Turbomachinery,1994,116(4):721-729.
[7]	MEHENDALE A B,HAN J C,OU S,et al.Unsteady wake over a linear turbine blade cascade with air and CO₂ film injection:Part II:Effect on film effectiveness and heat transfer distributions[J].Journal of Turbomachinery,1994,116(4):730-737.
[8]	GAO Z,NARZARY D P,HAN J C.Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes[J].International Journal of Heat and Mass Transfer,2008,51(9):2139-2152.
[9]	MHETRAS S,HAN J C.Effect of unsteady wake on full coverage film-cooling effectiveness for a gas turbine blade[C]//Proceedings of 9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference.Reston:AIAA,2006,2:1382-1398.
[10]	GOMES R A,NIEHUIS R.Film cooling effectiveness measurements with periodic unsteady inflow on highly loaded blades with main flow separation[J].Journal of Turbomachinery,2011,133(2):021019.
[11]	ARDEY S,FOTTNER L.A systematic experimental study on the aerodynamics of leading edge film cooling on a large scale high pressure turbine cascade[C]//Proceedings of the 1998 International Gas Turbine & Aeroengine Congress & Exhibition.Fairfield,NJ:ASME,1998.
[12]	MONTOMOLI F,MASSINI M,ADAMI P,et al.Effect of incidence angle with wake passing on a film cooled leading edge:A numerical study[J].International Journal for Numerical Methods in Fluids,2010,63(12):1359-1374.
[13]	BENABLED M,AZZI A,JUBRAN B A.Numerical investigation of the influence of incidence angle on asymmetrical turbine blade model showerhead film cooling effectiveness[J].Heat and Mass Transfer,2010,46(8-9):811-819.
[14]	MARTELLI F,ADAMI P.Unsteady aerodynamics and heat transfer in transonic turbine stages modelling approaches[C]//8th International Congress of Fluid Dyanmics & Propulsion,2006:14-17.
[15]	ADAMI P,MONOTOMOLI F,BELARDINI E,et al.Interaction between wake and film cooling jets:Numerical analysis[C]//Proceedings of the ASME Turbo Expo 2004:Volume 5B:Turbomachinery;Axial Flow Turbine Aerodynamics;Design Methods and CFD Modelling for Turbomachinery;Turbomachines and the Environment.New York:ASME,2004:1053-1063.
[16]	蒋雪辉,赵晓路.非定常尾迹对叶片头部气膜冷却的影响[J].航空动力学报,2005,20(4):540-544. JIANG X H,ZHAO X L.The effect of unsteady wake on leading edge film cooling[J].Journal of Aerospace Power,2005,20(4):540-544(in Chinese).
[17]	谭晓茗,朱兴丹,郭文,等.涡轮叶片前缘气膜冷却换热实验[J].航空动力学报,2014,29(11):2672-2678. TAN X M,ZHU X D,GUO W,et al.Heat transfer experiment on film cooling of turbine blade leading edge[J].Journal of Aerospace Power,2014,29(11):2672-2678(in Chinese).
[18]	张宗卫,朱惠人,刘聪,等.全气膜冷却叶片表面换热系数和冷却效率研究[J].西安交通大学学报,2012,46(7):103-107. ZHANG Z W,ZHU H R,LIU C,et al.Heat transfer coefficient and film cooling effectiveness on a full-film cooling vane[J].Journal of Xi'an Jiaotong University,2012,46(7):103-107(in Chinese).
[19]	周勇,赵晓路,徐建中.非定常激波对气膜冷却影响的数值模拟[J].工程热物理学报,2007,28(6):933-935. ZHOU Y,ZHAO X L,XU J Z.Numerical simulation of the unsteady effect of upstream shocks on film-cooling in a 1+1/2 turbine stage[J].Journal of Engineering Thermophysics,2007,28(6):933-935(in Chinese).
[20]	周莉,张鑫,蔡元虎.非定常尾迹宽度对气膜冷却效果的影响[J].中国电机工程学报,2011,31(29):97-102. ZHOU L,ZHANG X,CAI Y H.Effect of unsteady wake width on the film-cooling effectiveness for a gas turbine blade[J].Proceedings of the CSEE,2011,31(29):97-102(in Chinese).
[21]	周莉,韦威,蔡元虎.非定常尾迹输运对动叶气膜冷却流场影响[J].航空动力学报,2012,27(8):1696-1703. ZHOU L,WEI W,CAI Y H.Effect of unsteady wake transportation on film cooling flowfield of rotating turbine blade[J].Journal of Aerospace Power,2012,27(8):1696-1703(in Chinese).
[22]	SCHULTE V,HODSON H P.Unsteady wake-induced boundary layer transition in high lift LP turbines[J].Journal of Turbomachinery,1998,120(1):28-35.
[23]	SCHULTE V,HODSON H P.Wake-separation bubble interaction in low pressure turbines:AIAA-1994-2931[R].Reston:AIAA,1994:1-8.
[24]	NARZARY D P,GAO Z,MHETRAS S,et al.Effect of unsteady wake on film-cooling effectiveness distribution on a gas turbine blade with compound shaped holes[C]//Proceedings of the ASME Turbo Expo 2007-Power for Land,Sea,and Air.New York:ASME,2007,4 PART A:79-91.