Volume 29 Issue 6
Jun.  2014
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2014  >  (6): 1301-1311
LU Shao-peng, CHI Zhong-ran, WANG Long-fei, CAI Le, WANG Song-tao, FENG Guo-tai, WANG Zhong-qi. Influence of turbine stator blade profiles and film cooling holes optimization on the aerodynamic and cooling performances[J]. Journal of Aerospace Power, 2014, (6): 1301-1311. doi: 10.13224/j.cnki.jasp.2014.06.007
Citation: LU Shao-peng, CHI Zhong-ran, WANG Long-fei, CAI Le, WANG Song-tao, FENG Guo-tai, WANG Zhong-qi. Influence of turbine stator blade profiles and film cooling holes optimization on the aerodynamic and cooling performances[J]. Journal of Aerospace Power, 2014, (6): 1301-1311. doi: 10.13224/j.cnki.jasp.2014.06.007
shu

Influence of turbine stator blade profiles and film cooling holes optimization on the aerodynamic and cooling performances

doi: 10.13224/j.cnki.jasp.2014.06.007

  • 1. School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China;

  • 2. Department of Thermal Engineering, Tsinghua University, Beijing 100084, China

  • Received Date: 2013-03-22
  • Publish Date: 2014-06-28
    Abstract
  • To study the influence of blade profiles and film cooling holes' parameter changes on the performance of the turbine blade, a blade stator with multi-row film cooling holes was optimized by multi-objective optimization algorithm to get the Pareto set; the overall performance of the blade was improved. The maximum aerodynamic efficiency increased by 0.35%; the maximum wall average temperature decrease was 0.74%; the maximum decrease of the high temperature function was 45.71%. The result shows that the increase of the backward curved angle can reduce the blade loss and second flow loss. The cooling effect improvement of the region near the leading edge is mainly due to the direction change of the film cooling holes near the leading edge stagnation point, as the direction change makes the cooling gas distribution reasonable.

     

    • FullText(HTML)
  • loading
    • References(20)
  • [1]
    Blazek J.Aerodynamic shape optimization of turbomachinery cascade.AIAA-97-2131,1997.
    [2]
    Marcello M,Raffaele T.Optimum aero-thermal design of turbo machinery blading systems accounting for variable operating conditions.ASME Paper GT2003-38629,2003.
    [3]
    袁新,林智荣,赖宇阳,等.透平叶片的气动优化设计系统[J].热力透平,2004,33(1):8-13. YUAN Xin,LIN Zhirong,LAI Yuyang,et al.Aerodynamic optimization system for turbine blade design[J].Thermal Turbine,2004,33(1):8-13.(in Chinese)
    [4]
    冯国泰,顾中华,温风波,等.燃气涡轮机气冷涡轮气动设计体系设计思想及其应用[J].工程热物理学报,2009,30(11):1841-1848. FENG Guotai,GU Zhonghua,WEN Fengbo,et al.Aerodynamic design system and ideology of air-cooled turbine and its application to gas turbines[J].Journal of Engineering Thermo Physics,2009,30(11):1841-1848.(in Chinese)
    [5]
    王婧超,李立州,岳珠峰.涡轮叶片的多学科设计优化系统[J].航空动力学报,2007,22(1):23-29. WANG Jingchao,LI Lizhou,YUE Zhufeng.Multidisciplinary optimization design system for turbine blade[J].Journal of Aerospace Power,2007,22(1):23-29.(in Chinese)
    [6]
    Brian H D,Igor N E,Helmut S,et al.Parallel thermo elasticity optimization of 3-D serpentine cooling passages in turbine blades.ASME Paper GT2003-38180,2003.
    [7]
    Talya S S,Chattopadhyay A,Rajadas J N.Multidisciplinary analysis and design optimization procedure for cooled gas turbine blades.AIAA-2000-4877,2000.
    [8]
    虞跨海,杨茜,倪俊,等.基于响应面的涡轮叶片冷却通道设计优化[J].航空学报,2009,30(9):1630-1634. YU Kuahai,YANG Xi,NI Jun,et al.Cooling passage design optimization of turbine blade based on response surface methodology[J].Acta Aeronautica et Astronautica Sinica,2009,30(9):1630-1634.(in Chinese)
    [9]
    舒彪,韩前鹏,邓家褆.基于多学科涡轮叶片气动设计优化[J].南京航空航天大学学报,2005,37(6):714-719. SHU Biao,HAN Qianpeng,DENG Jiati.Aerodynamic design optimization of turbine blade based on multidiscipline[J].Journal of Nanjing University of Aeronautics and Astronautics,2005,37(6):714-719.(in Chinese)
    [10]
    潘尚能,罗建桥.涡轮多学科优化中的气动设计技术探讨[J].航空动力学报,2012,27(3):635-643. PAN Shangneng,LUO Jianqiao.Aerodynamic design technology in multidisciplinary optimization for turbine[J].Journal of Aerospace Power,2012,27(3):635-643.(in Chinese)
    [11]
    Jong S L,Malak F M.Enhanced film cooling effectiveness with new shaped holes.ASME Paper GT2010-22774,2010.
    [12]
    姚玉,张靖周,何飞,等.涡轮叶片吸力面上收敛缝形孔气膜冷却效率的数值研究[J].航空学报,2010,31(6):1115-1120. YAO Yu,ZHANG Jingzhou,HE Fei,et al.Numerical investigation on film cooling effectiveness of converging slot hole at turbine blade suction surface[J].Acta Aeronautica et Astronautica Sinica,2010,31(6):1115-1120.(in Chinese)
    [13]
    李广超,朱惠人,白江涛,等.气膜孔布局对前缘气膜冷却效率影响的实验[J].推进技术,2008,29(2):153-157. LI Guangchao,ZHU Huireng,BAI Jiangtao,et al.Experimental investigation of film cooling effectiveness on leading edge with various geometries[J].Journal of Propulsion Technology,2008,29(2):153-157.(in Chinese)
    [14]
    卢少鹏,迟重然,温风波,等.考虑气膜冷却的涡轮静叶多目标优化[J].工程热物理学报,2013,34(6):1036-1041. LU Shaopeng,CHI Zhongran,WEN Fengbo,et al.Multi-objective optimization of turbine blades considering film cooling[J].Journal of Engineering Thermophysics,2013,34(6):1036-1041.(in Chinese)
    [15]
    迟重然.气冷涡轮叶片的传热设计.哈尔滨:哈尔滨工业大学,2011. CHI Zhongran.Heat transferring design for air-cooled turbine blades.Harbin:Harbin Institute of Technology,2011.(in Chinese)
    [16]
    Sridhar M,Sunnam S,Goswami S,et al.CFD aerodynamic performance validation of a two-stage high pressure turbine.ASME Paper GT2011-45569,2011.
    [17]
    曾军,王丽,王彬.GE公司E3涡轮部件全三维流场计算与分析.三亚:ANSYS 2011中国用户大会优秀论文集,2011.
    [18]
    董平.航空发动机气冷涡轮叶片的气热耦合数值模拟研究.哈尔滨:哈尔滨工业大学 2009. DONG Ping.Research on conjugate heat transfer simulation of aero turbine engine air-cooled vane.Harbin:Harbin Institute of Technology,2009.(in Chinese)
    [19]
    Kalila E E,Lenahan D T,Thomas T T.High pressure turbine test hardware detail design report.NASA CR-167955,1982.
    [20]
    Timko L P.Energy efficient engine high pressure turbine component test performance report.NASA CR-168289,1990.
    • 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(1509.0KB)
    XML

    Article Metrics

    Article views (2290) PDF downloads(1066) 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