Volume 34 Issue 10
Oct.  2019
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2019  >  34(10): 2131-2139
WANG Weijie, MA Haiteng, ZHANG Qiang. Cooling and heat transfercharacteristics of high-pressure turbine blade with cutback squealer tip[J]. Journal of Aerospace Power, 2019, 34(10): 2131-2139. doi: 10.13224/j.cnki.jasp.2019.10.006
Citation: WANG Weijie, MA Haiteng, ZHANG Qiang. Cooling and heat transfercharacteristics of high-pressure turbine blade with cutback squealer tip[J]. Journal of Aerospace Power, 2019, 34(10): 2131-2139. doi: 10.13224/j.cnki.jasp.2019.10.006
shu

Cooling and heat transfercharacteristics of high-pressure turbine blade with cutback squealer tip

doi: 10.13224/j.cnki.jasp.2019.10.006
  • 1.

    School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240,China

  • 2.

    School of Mechanical Engineering,Shanghai Jiao Tong University,Shanghai 200240,China

  • 3.

    University of Michigan-Shanghai Jiao Tong University Joint Institute,Shanghai 200240,China

  • Received Date: 2019-04-08
  • Publish Date: 2019-10-28
    Abstract
  • In order to study the surface heat transfer of turbine blades with cutback squealer tip, surface heat transfer coefficient was investigated experimentally through a transient wind tunnel experiment for an uncooled blade and a blade with dust purge holes. The experimental outcome was compared with the numerical simulation result. The uncertainty of the experiment was less than 5%. By analyzing the over tip leakage (OTL) flow condition, it revealed that on the uncooled blade tip, due to the cavity vortex and the separation bubbles, high surface heat transfer coefficient values were scattered on squealer rims of both pressure side (PS) and suction side (SS), and on cavity floor near the leading edge. A strip of low surface heat transfer coefficient values appeared onthe PS of the second half cavity. In the cooled case, coolant flow from dust purge holes was separated into two parts. The high-energy fluid merged into the OTL flow, resulting in multiple high surface heat transfer coefficient distributions on the SS rim, while the low-energy fluid flowed backward along the SS of the cavity. Cooling effectiveness can reach over 0.4 in this region.

     

    • FullText(HTML)
  • loading
    • References(25)
  • [1]
    DENTON J D.Loss mechanisms in turbomachines［R］.ASME Paper 93-GT-435,1993.
    [2]
    MOORE J,TILTON J S.Tip leakage flow in a linear turbine cascade［J］.Journal of Turbomachinery,1988,110(1):18-26.
    [3]
    SJOLANDER S A,CAO D.Measurements of the flow in an idealized turbine tip gap［R］.ASME Paper 94-GT-74,1994.
    [4]
    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.
    [5]
    KRISHNABABU S K,NEWTON P J,DAWES W N,et al.Aerothermal investigations of tip leakage flow in axial flow turbines:Part Ⅰ effect of tip geometry and tip clearance gap［J］.Journal of Turbomachinery,2009,131(1):011006.1-011006.14.
    [6]
    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［J］.航空动力学报,2013,28(10):2316-2325.ZHONG Fangpan,ZHOU Chao,ZHOU Kai.Aerodynamic performance of tip leakage flow of two different blade tips in transonic turbine［J］.Journal of Aerospace Power,2013,28(10):2316-2325.(in Chinese)
    [7]
    杨佃亮,丰镇平.凹槽对动叶尖部流动和换热的影响［J］.工程热物理学报,2007,28(6):936-938.YANG Dianliang,FENG Zhenping.Study on tip leakage flow and heat transfer for a squealer tip blade［J］.Journal of Engineering Thermophysics,2007,28(6):936-938.(in Chinese)
    [8]
    杜昆,宋立明,李军.凹槽状叶顶涡轮叶片传热特性的数值研究［J］.推进技术,2014,35(5):618-623.DU Kun,SONG Liming,LI Jun.Numerical investigations on heat transfer characteristics of turbine blade with squealer tip［J］.Journal of Propulsion Technology,2014,35(5):618-623.(in Chinese)
    [9]
    MHETRAS S,NARZARY D,GAO Z,et al.Effect of a cutback squealer and cavity depth on film-cooling effectiveness on a gas turbine blade tip［J］.Journal ofTurbomachinery,2008,130(2):021002.1-021002.11.
    [10]
    成锋娜,常海萍,张镜洋,等.突肩叶尖尾缘开槽对间隙流动换热特性的影响［J］.航空动力学报,2016,31(2):383-390.CHENG Fengna,CHANG Haiping,ZHANG Jingyang,et al.Tip leakage flow and heat transfer characteristics with effect of trailing edgecutback on squealer tip［J］.Journal of Aerospace Power,2016,31(2):383-390.(in Chinese)
    [11]
    虞跨海,杨茜,岳珠峰.排尘孔涡轮冷却叶片叶尖流动与传热研究［J］.机械工程学报,2012,48(8):122-127.YU Kuahai,YANG Xi,YUE Zhufeng.Tip flow and heat transfer prediction of cooling blade with dirt purge holes［J］.Journal of Mechanical Engineering,2012,48(8):122-127.(in Chinese)
    [12]
    HOHLFELD E M,CHRISTOPHEL J R,COUCH E L,et al.Predictions of cooling from dirt purge holes along the tip of a turbine blade［R］.ASME Paper GT2003-38251,2003.
    [13]
    ZHANG X,YANG Z,TIAN S,et al.Numerical study of the film cooling with discrete-hole arrangement on a cut back squealer blade tip［R］.ASME Paper GT2015-43877,2015.
    [14]
    MA H,ZHANG Q,HE L,et al.Cooling injection effect on a transonic squealer tip:Part Ⅰ experimental heat transfer results and CFD validation［J］.Journal of Engineering for Gas Turbines and Power,2017,139(5):052506.1-052506.9.
    [15]
    MA H,ZHANG Q,HE L,et al.Cooling injection effect on a transonic squealer tip:Part Ⅱ analysis of aerothermal interaction physics［J］.Journal of Engineering for Gas Turbines and Power,2017,139(5):052507.1-052507.11.
    [16]
    ZHENG R,LI M,WANG Z,et al.Control of blow-down wind tunnel using combined extended and nonlinear predictive filters［R］.ASME Paper GT2015-42908,2015.
    [17]
    XI J,ZHANG Q,LI M,et al.Advanced flow control for supersonic blowdown wind tunnel using extended Kalman filter［J］.Journal of Dynamic Systems,Measurement,and Control,2015,137(1):014501.1-014501.12.
    [18]
    EVANS R O,DAWES WN,ZHANG Q.Application of design of experiment to a gas turbine cascade test cell［R］.ASME Paper GT2013-94314,2013.
    [19]
    陈韡.对常规涡轮叶片瞬态传热测试及分析方法的改进［D］.上海:上海交通大学,2013.CHEN Wei.Improvements on conventional transient thermal measurement on turbine blade［D］.Shanghai:Shanghai JiaoTong University,2013.(in Chinese)
    [20]
    OLDFIELD M L.Impulse response processing of transient heat transfer gauge signals［J］.Journal of Turbomachinery,2008,130(2):021023.1-021023.9.
    [21]
    O’DOWD D O,ZHANG Q,HE L,et al.Comparison of heat transfer measurement techniques on a transonic turbine blade tip［J］.Journal of Turbomachinery,2011,133(2):021028.1-021028.10.
    [22]
    ZHANG Q,HE L,WHEELER A P S,et al.Overtip shock wavestructure and its impact on turbine blade tip heat transfer［J］.Journal of Turbomachinery,2011,133(4):041001.1-041001.8.
    [23]
    ZHONG F,ZHOU C,MA H,et al.Heat transfer of winglet tips in a transonic turbine cascade［J］.Journal of Engineering for Gas Turbines and Power,2016,138(1):012605.1-012605.13.
    [24]
    ZHANG Q,O’DOWD D O,HE L,et al.Transonic turbine blade tip aerothermal performance with different tip gaps:Part Ⅰ tip heat transfer［J］.Journal ofTurbomachinery,2011,133(4):041027.1-041027.9.
    [25]
    ZHANG Q,HE L.Impact of wall temperature on turbine blade tip aerothermal performance［J］.Journal ofEngineering for Gas Turbines and Power,2014,136(5):052602.1-052602.10.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(955.0KB)
    XML

    Article Metrics

    Article views (755) PDF downloads(397) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return