开槽尾流板对跨声速涡轮平面叶栅流场影响的实验

巩昊; 徐惊雷; 陈宇

doi:10.13224/j.cnki.jasp.2018.12.027

开槽尾流板对跨声速涡轮平面叶栅流场影响的实验

doi: 10.13224/j.cnki.jasp.2018.12.027

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，南京 210016

计量
- 文章访问数: 516
- HTML浏览量: 5
- PDF量: 369
- 被引次数: 0
出版历程
- 收稿日期: 2017-11-26
- 刊出日期: 2018-12-28

Experiment on effects of slotted tailboard on flow field of transonic turbine linear cascade

摘要

摘要: 采用数值计算和实验相结合的方式研究了开槽尾流板对跨声速涡轮平面叶栅流场周期性的影响。通过数值计算研究了不同开孔率（10%、15%、30%、50%）和偏转角度（70°、71°、72°）下尾流板对叶片表面及叶栅流道出口压力分布的影响，并通过实验验证了尾流板对流道出口流场周期性的改善作用。结果表明：无尾流板时叶片表面压力分布明显偏离周期性计算结果，且流道出口压力分布的周期性误差较大；尾流板偏转角度和开孔率会影响叶片表面及叶栅流道出口的压力分布，适当调节尾流板参数能改善流场周期性；安装开孔率为50%，偏转角度为70°的尾流板时各流道出口的压力分布一致性最好且最接近周期性计算结果，计算和实验结果的周期性误差较无尾流板时分别降低47.6%和28.1%。
- 叶栅流场周期性 /
- 开槽尾流板 /
- 开孔率 /
- 偏转角度 /
- 平面叶栅风洞实验
Abstract: Numerical and experimental investigations were performed to study the effect of the slotted tailboard on the periodicity of transonic gas turbine cascade. Computational fluid dynamics was employed to study the effect of tailboards for pressure distributions of the blades and cascade passage exits with different void ratios (10%, 15%, 30%, 50%) and pitch angles (70°, 71°, 72°), meanwhile experiment was performed to verify that the tailboard improved the periodicity of cascade passage exit flow field. Results showed that, without tailboard, pressure distributions of the blades deviated from the periodic result apparently and the periodicity error of the cascade passage exits was quite large. Pressure distributions were affected by tailboards with different void ratios and pitch angles, besides, the periodicity of the flow field can be improved with a tailboard of appropriate parameters. Pressure distributions of cascade passage exits were much closer to each other and the periodic result with void ratio of 50% and pitch angle of 70° tailboard when compared with no tailboard condition, while the periodicity errors of numerical and experimental results were reduced by 47.6% and 28.1%, respectively.
- periodicity of cascade flow field /
- slotted tailboard /
- void ratio /
- pitch angle /
- linear cascade wind tunnel experiment

HTML

参考文献(21)

[1]	胡骏.航空叶片机原理［M］.北京:国防工业出版社,2014.
[2]	楚武利,刘前智,胡春波.航空叶片机原理［M］.西安:西北工业大学出版社,2009.
[3]	刘壮,阚晓旭,陆华伟.跨声速涡轮平面叶栅气动性能实验研究［J］.大连海事大学学报,2013,39(1):123-127.LIU Zhuang,KAN Xiaoxu,LU Weihua.Experimental investigation of aerodynamic parameters in transonic turbine linear cascade［J］.Journal of Dalian Maritime University,2013,39(1):123-127.(in Chinese)
[4]	龚建波,俞镔,朱俊强.超音速涡轮叶栅气动性能实验及分析［J］.工程热物理学报,2006,27(增刊1):125-128.GONG Jianbo,YU Bin,ZHU Junqiang.The experiment and analyse on the aerodynamic performance of transonic turbine cascades［J］.Journal of Engineering Thermophysics,2006,27(Suppl.1):125-128.(in Chinese)
[5]	陈升,邱超,宋华芬.涡轮平面叶栅变几何实验研究［J］.热能动力工程,2011,26(1):7-12.CHEN Sheng,QIU Chao,SONG huafen.Variable geometry experimental study of a turbine plane cascade［J］.Journal of Engineering for Thermal Energy and Power,2011,26(1):7-12.(in Chinese)
[6]	刘建明,王东,马永峰.低压涡轮导向叶片平面叶栅实验及数值模拟［J］.航空发动机,2012,38(6):20-23.LIU Jianming,WANG Dong,MA Yongfeng.Experiment and numerical simulation of low pressure turbine guide vane planar cascade［J］.Aeroengine,2012,38(6):20-23.(in Chinese)
[7]	雒伟伟,王会社,赵晓路.跨声速缩放型流道涡轮平面叶栅流场的实验研究［J］.工程热物理学报,2013,34(7):1229-1232.HE Weiwei,WANG Huishe,ZHAO Xiaolu.Experiment investigation on the flow characteristic in a transonic convergent-divergent turbine cascade［J］.Journal of Engineering Thermophysics,2013,34(7):1229-1232.(in Chinese)
[8]	RONA A,GOSTELOW J P.Performance of slotted end wall linear cascade tunnels at off-design conditions［R］.AIAA-2005-0908,2005.
[9]	陈宇,徐惊雷,黄帅，等.平面叶栅尾流板开孔率对跨声速涡轮叶栅流道影响的数值分析［J］.航空动力学报,2018,33(1):209-214.CHEN Yu,XU Jinglei,HUANG Shuai,et al.Numerical study on the effect of the linear cascade slotted tailboard void ratio on the passage of transonic gasturbine cascade［J］.Journal of Aerospace Power,2018,33(1):209-214.(in Chinese)
[10]	NASIR S,CARULLO J S,NG W F,et al.Effects of large scale high freestream turbulence and exit reynolds number on turbine vane heat transfer in a transonic cascade［J］.Journal of Turbomachinery,2009,131(2):021021.1-021021.11.
[11]	HOLLEY B M,LANGSTON L S.Surface shear stress and pressure measurements in a turbine cascade［J］.Journal of Turbomachinery,2009,131(3):031014.1-031014.8.
[12]	CORRIVEAU D.Influence of loading distribution on the performance of transonic high pressure turbine blades［J］.Journal of Turbomachinery,2007,129(3):809-820.
[13]	CARULLO J S.The effects of freestream turbulence,turbulence length scale,and exit reynolds number on turbine blade heat transfer in a transonic cascade［J］.Journal of Turbomachinery,2011,133(1):1077-1089.
[14]	CHAO Z,HODSON H,Tibbott I,et al.Effects of winglet geometry on the aerodynamic performance of tip leakage flow in a turbine cascade［J］.Journal of Turbomachinery,2013,135(5):1263-1274.
[15]	VOLINO R J.Control of tip leakage in a high pressure turbine cascade using tip blowing［R］.ASME Paper GT2016-56511,2016.
[16]	PAPA F,MADANAN U,GOLDSTEIN R J.Modeling and measurements of heat/mass transfer in a linear turbine cascade［J］.Journal of Turbomachinery,2017,139(9):091002.1-091002.12.
[17]	RONA A,PACIORRI R,GERON M.Slot width augmentation in a slotted-wall transonic linear cascade wind tunnel［R］.AIAA-2004-608,2004.
[18]	RONA A,PACIORRI R,GERON M.Design and testing of a transonic linear cascade tunnel with optimized slotted walls［J］.Journal of Turbomachinery,2006,128(1):23-34.
[19]	PACIORRI R,SABETTA F,RONA A.Wave reflection on porous walls:numerical modelling and application to transonic wind tunnels［R］.AIAA-2002-1060,2002.
[20]	RONA A,GOSTELOW J P.Performance margins of non-reflecting slotted walls in a transonic linear cascade tunnel［R］.ASME Paper GT2006-91057,2006.
[21]	RONA A,GOSTELOW J P,PACIORRI R,et al.Wall interference in the discharge flow in a linear cascade wind tunnel［R］.AIAA-2003-455,2003.