气热耦合条件下涡轮静叶三维优化

推进技术 ›› 2014, Vol. 35 ›› Issue (3): 356-364.

气热耦合条件下涡轮静叶三维优化

卢少鹏¹,迟重然²,罗磊¹,蔡乐¹,王松涛¹,冯国泰¹,王仲奇¹

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

发布日期:2021-08-15
作者简介:卢少鹏(1984—),男,博士生,研究领域为气冷涡轮叶片气动设计与优化。E-mail:txyxlsp@163.com

Conjugate Heat Transfer 3-D Optimization for Turbine Stator

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

Published:2021-08-15

摘要/Abstract

摘要： 为解决涡轮静叶尾缘烧蚀问题并提升气动效率,采用气热耦合优化的方法对该叶片进行优化,优化分为对叶型优化以及对弯叶片优化两部分。优化结果显示,对叶型进行优化时由于叶型变化以及冷气流量增加2.68%导致叶片平均温度降低4.15%,最高温度下降61.7K,气动效率提升0.17%；对弯叶片进行优化时,顶部正弯效果明显,冷气流量增加0.11%,叶片平均温度下降2.4%,最高温度下降10.6K,气动效率提升0.16%。通过分析,对于该径高比较小的叶片,无论是叶型变化还是弯叶片变化,低能流体由端区进入主流导致的端区损失降低和激波损失的降低是导致气动效率提升的主要原因；冷气流量加大以及端区二次流减弱是造成叶片温度场降低的主要原因。 

关键词: 涡轮;弯叶片;气热耦合;多目标优化 

Abstract: To avoid the turbine blade tail edge ablation and improve the aerodynamic performance, conjugate heat transfer optimization was used to change the parameters of blade profiles and bowed blade. The blade profiles optimization and bowed blade optimization were carried out independently. The results show that during the blade profile optimization as the blade profiles are changed and the mass flow of the coolant increases by 2.68%, the average temperature of the blade decreases by 4.15% and the maximum temperature decreases by 61.7K, also the aerodynamic efficiency increases by 0.17%. During the process of bowed blade optimization, the effect of blade positive curving near the tip is obvious, the mass flow of the coolant increases by 0.11%, the average temperature decreases by 2.4%, the maximum temperature decreases by 10.6K and the aerodynamic efficiency increases by 0.16%. For the blade with small diameter-blade height ratios, there are two major factors influencing the efficiency, the first one is the decrease of the shock loss and the second one is the decrease of the end wall loss as the low energy fluids near the end wall moves into the mainstream.The increase of the coolant mass flow and the reduction of secondary flow are the major factors lowering the blade temperature.

Key words: Turbines; Bowed blade; Conjugate heat transfer; Multi-objective optimization

卢少鹏,迟重然,罗磊,蔡乐,王松涛,冯国泰,王仲奇. 气热耦合条件下涡轮静叶三维优化[J]. 推进技术, 2014, 35(3): 356-364.

LU Shao-peng¹,CHI Zhong-ran²,LUO Lei¹,CAI Le¹, WANG Song-tao¹,FENG Guo-tai¹,WANG Zhong-qi¹. Conjugate Heat Transfer 3-D Optimization for Turbine Stator[J]. Journal of Propulsion Technology, 2014, 35(3): 356-364.

参考文献

[1] 尚仁操, 乔渭阳, 许开富.气冷涡轮叶片气热耦合数值模拟研究[J].机械设计与制造, 2007,2(12):11-13.
[2] 董平, 黄洪雁, 冯国泰.高压燃气涡轮径向内冷叶片气热耦合的数值分析[J].航空动力学报, 2008,3(2):201-207
[3] 苏生, 刘建军, 安柏涛.内冷涡轮叶栅三维气热耦合数值模拟[J].航空动力学报, 2007,2(12):2018-2024.
[4] 胡捷,刘建军,江友钿.燃气轮机透平叶片气热耦合计算[J].航空动力学报, 2011,6,(2):349-354.
[5] 董平.航空发动机气冷涡轮叶片的气热耦合数值模拟研究[D].哈尔滨:哈尔滨工业大学, 2009.
[6] 王强.提高气冷涡轮气热耦合计算精度方法的研究[D].哈尔滨:哈尔滨工业大学, 2009.
[7] 张超.燃气透平导叶气热耦合实验与数值研究[D].北京:中国科学院工程热物理研究所, 2011.
[8] 尚仁操.涡轮叶片气热耦合计算和设计优化数值研究[D].西安:西北工业大学, 2007.
[9] Blazek J.Aerodynamic Shape Optimization of Turbo Machinery Cascade [R].AIAA-97-2131.
[10] Marcello Manna, Raffaele Tuccillo.Optimum Aero-Thermal Design of Turbo Machinery Blading Systems Accounting for Variable Operating Conditions[R].ASME GT2003-38629.
[11] Talya S S,Chattopadhyay A,Rajadas J N.Multidisciplinary Analysis and Design Optimization Procedure for Cooled Gas Turbing Blades [R].AIAA 2000-4877.
[12] 李立州, 王靖超, 吕震宙,等.涡轮叶片流固耦合协作优化方法[J].推进技术, 2008,9(5) 604-608.(LI Li-zhou, WANG Jing-chao, LU Zhen-zhou,et al.Collaborative Optimization Method for Fluid-Solid Coupling Problem of Turbine Blades[J].Journal of Propulsion Technology, 2008,9(5):604-608.
[13] 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, 2009,0(9):1630-1634.
[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[C].哈尔滨:中国工程热物理学会年会,2012.
[15] Sridhar Murari, Sunnam Sathish, Goswami Shraman, et al.CFD Aerodynamic Performance Validation of A Two-Stage High Pressure Turbine [R].ASME GT2011-45569.