涡轮静叶叶型与气膜孔优化对气动与冷却性能影响

卢少鹏; 迟重然; 王龙飞; 蔡乐; 王松涛; 冯国泰; 王仲奇

doi:10.13224/j.cnki.jasp.2014.06.007

涡轮静叶叶型与气膜孔优化对气动与冷却性能影响

doi: 10.13224/j.cnki.jasp.2014.06.007

1. 哈尔滨工业大学能源科学与工程学院, 哈尔滨 150001;
2. 清华大学热能工程系, 北京 100084

详细信息

作者简介:
卢少鹏（1984- ），男，山东潍坊人，博士，主要从事涡轮气动设计与优化.

中图分类号: V232.4
计量
- 文章访问数: 2297
- HTML浏览量: 234
- PDF量: 1066
- 被引次数: 0
出版历程
- 收稿日期: 2013-03-22
- 刊出日期: 2014-06-28

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

1. School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China;
2. Department of Thermal Engineering, Tsinghua University, Beijing 100084, China

摘要

摘要: 为研究气膜冷却涡轮叶片中叶型与气膜孔参数变化对涡轮静叶性能的影响，利用气膜冷却涡轮多目标优化平台对存在多列气膜孔的静叶进行多目标优化.获得在优化变量允许范围内针对气动效率与传热效果以及高温目标函数的Pareto前沿解集，整体性能得到了提高，不同方案中气动效率最高提升0.35%，叶片表面温度最大下降0.74%，高温函数降低的最大幅值为45.71%.结果表明：气动效率提升的主要原因是后弯角的提升使得叶型和二次流损失下降；接近驻点处前缘气膜孔方向的改变导致的冷气分流是叶片根部和前缘附近压力侧的冷却情况得到改善的主要原因.
- 涡轮 /
- 气膜冷却 /
- 喷射角度 /
- 多目标优化 /
- Pareto解集
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.
- turbine /
- film cooling /
- injection angle /
- multi-objective /
- Pareto solution set

HTML

参考文献(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.