冷气对多级涡轮翘曲S1流面优化的影响

推进技术 ›› 2016, Vol. 37 ›› Issue (3): 459-470.

冷气对多级涡轮翘曲S1流面优化的影响

王龙飞,王松涛,罗磊,温风波,崔涛

哈尔滨工业大学能源科学与工程学院发动机气体动力研究中心，黑龙江哈尔滨 150001,哈尔滨工业大学能源科学与工程学院发动机气体动力研究中心，黑龙江哈尔滨 150001,哈尔滨工业大学能源科学与工程学院发动机气体动力研究中心，黑龙江哈尔滨 150001,哈尔滨工业大学能源科学与工程学院发动机气体动力研究中心，黑龙江哈尔滨 150001,哈尔滨工业大学能源科学与工程学院发动机气体动力研究中心，黑龙江哈尔滨 150001

发布日期:2021-08-15
作者简介:王龙飞，男，博士生，研究领域为气冷涡轮的叶片冷却设计。
基金资助:
国家自然科学基金委创新研究群体(51121004；51206034)。

Effects of Coolant on Twisted S1 Stream Surface Optimization in Multi-Stage Turbine

Aerodynamic Research Center of Engine Power，School of Energy Science and Engineering， Harbin Institute of Technology，Harbin 150001，China,Aerodynamic Research Center of Engine Power，School of Energy Science and Engineering， Harbin Institute of Technology，Harbin 150001，China,Aerodynamic Research Center of Engine Power，School of Energy Science and Engineering， Harbin Institute of Technology，Harbin 150001，China,Aerodynamic Research Center of Engine Power，School of Energy Science and Engineering， Harbin Institute of Technology，Harbin 150001，China and Aerodynamic Research Center of Engine Power，School of Energy Science and Engineering， Harbin Institute of Technology，Harbin 150001，China

Published:2021-08-15

摘要/Abstract

摘要： 设计以翘曲S1流面优化为核心的多级涡轮气动优化流程，研究气膜冷气、尾缘冷气、端壁冷气对优化可靠性和有效性的影响。该流程能够对多种叶高处带叶片冷气的多级翘曲S1流面进行并行优化，提高了优化的可靠性。对两级高压涡轮给定三种叶片冷气方案:包括气膜冷气和尾缘冷气的叶身冷气、气膜冷气、无叶片冷气，分别进行翘曲S1流面优化设计。优化后翘曲S1流面平均气动效率分别提高0.20%、0.38%、0.07%，涡轮气动效率分别提高0.33%、0.32%、0.26%，优化的可靠性较好。分析可知，气膜冷气增强了径向二次流动，降低了优化的有效性，尾缘冷气则部分削弱了气膜冷气的消极作用；下端壁冷气较上端壁冷气对端区二次流的作用强，因此前者对翘曲S1流面优化的积极作用更好。

关键词: 气膜冷气；尾缘冷气；端壁冷气；翘曲流面优化；多级涡轮；可靠性；有效性

Abstract: Multi-stage turbine aerodynamics optimization process was designed with the core of twisted S1 stream surface optimization，and the effects of film cooling air，trailing edge coolant，endwall coolant were researched on validity and reliability of the twisted S1 stream surface optimization. This process could advance parallel optimization for multi-stage twisted S1 stream surface with blade coolant in variety of blade height，which can improve twisted S1 stream surface optimization reliability. There were three blade coolant plans for a two-stage high pressure turbine: blade body coolant including of film cooling air and trailing edge coolant，film cooling air，without blade coolant，and the design of twisted S1 stream surface optimization was conducted. The average aerodynamic efficiency of twisted S1 stream surface increased by 0.20%，0.38%，0.07% and turbine aerodynamics efficiency increased by 0.34%，0.32%，0.28%，respectively. The optimization reliability was good. After analysis it is concluded that，film cooling air enhances radial secondary flow and then decreases the optimization validity，while trailing edge coolant weakens the negative effect of film cooling air partially. The bottom endwall coolant has more effect on secondary flow near endwall region than top endwall coolant，so the former plays a better positive role on S1 stream surface optimization.

Key words: Film cooling air；Trailing edge coolant；Endwall coolant；Twisted stream surface optimization；Multi-stage turbine；Validity；Reliability

王龙飞,王松涛,罗磊,温风波,崔涛. 冷气对多级涡轮翘曲S1流面优化的影响[J]. 推进技术, 2016, 37(3): 459-470.

WANG Long-fei,WANG Song-tao,LUO Lei,WEN Feng-bo,CUI Tao. Effects of Coolant on Twisted S1 Stream Surface Optimization in Multi-Stage Turbine[J]. Journal of Propulsion Technology, 2016, 37(3): 459-470.

参考文献

[1] 刘高联. 平面叶栅气动设计的最优化理论[J]. 力学学报, 1980,10(4): 337-346.
[2] 樊会元, 王尚锦, 席光. 透平机械叶片的遗传优化设计[J]. 航空学报, 1999, 20(1): 47-51.
[3] Blazek J. Aerodynamic Shape Optimization of Turbomachinery Cascade[R]. AIAA 97-2131.
[4] Dennis B H, Dulikravieh G S, Han Z X. Constrained Shape Optimization of Airfoil Cascades Using a Navier-Stokes Solver and a Genetic/SQP Algorithm[R]. ASME 99-GT-441.
[5] Dennis B H, Dulikravieh G S, Han Z X. Optimization of Turbomachinery Airfoils with a Genetic/Sequential Quadratic Programming Algorithm[J]. AIAA Journal of Propulsion and Power, 2001, 17(5): 1123-1128.
[6] Talya S S, Chattopadhyay A, Rajadas J N. Multidisciplinary Analysis and Design Optimization Procedure for Cooled Gas Turbine Blades[R]. AIAA 2000-4877.
[7] Talya S S, Chattopadhyay A, Rajadas J N. Multidisciplinary Design Optimization Procedure for Improved Design of a Cooled Gas Turbine Blade[J]. Engineering Optimization, 2002, 34(2): 175-194.
[8] Burguburu S, Pape A L. Improved Aerodynamic Design of Turbomachinery Bladings by Numerical Optimization[J]. Aerospace Science Technology, 2003, 7: 277-287.
[9] 高学林, 袁新. 叶轮机械全三维粘性气动优化设计系统[J]. 工程热物理学报, 2006, 26(4): 88-92.
[10] 陈志鹏, 袁新. 透平级通流部分全设计变量多目标优化设计[J]. 航空动力学报, 2009, 24(5): 1108-1113.
[11] 卢少鹏, 迟重然, 王松涛, 等. 考虑气膜冷却的涡轮静叶三维优化[J]. 推进技术, 2013, 34(5): 614-619. (LU Shao-peng, CHI Zhong-ran, WANG Song-tao, et al. Three-Dimensional Optimization of Turbine Blades Considering Film Cooling[J]. Journal of Propulsion Technology, 2013, 34(5): 614-619.)
[12] 卢少鹏, 迟重然, 罗磊, 等. 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-peng, CHI Zhong-ran, LUO Lei, et al. Conjugate Heat Transfer 3-D Optimization for Turbine Stator [J]. Journal of Propulsion Technology, 2014, 35(3): 356-364.)
[13] Wu C H. A General Theory of Three-Dimensional Flow in Subsonic and Supersonic Turbo Machines of Axial, Radial, and Mixed-Flow Types[R]. NACA-TN-2604, 1952.
[14] 罗磊, 卢少鹏, 王松涛, 等. 考虑冷气掺混流片边厚度的S1流面数值模拟[J]. 航空动力学报, 2014, 29(9): 2210-2221.
[15] 乔渭阳, 曾军, 曾文演, 等. 气膜孔喷气对涡轮气动性能影响的实验研究[J]. 推进技术, 2007, 28(1):14-19. (QIAO Wei-yang, ZENG Jun, ZENG Wen-yuan, et al. Experimental Studies for the Aerodynamic Loss in Gas Turbine with Film Cooling[J]. Journal of Propulsion Technology, 2007, 28(1):14-19.)
[16] 孙大伟, 乔渭阳, 曾军, 等. 尾缘喷气方式对涡轮叶栅气动性能的影响[J]. 推进技术, 2007, 28(6):641-646. (SUN Da-wei, QIAO Wei-yang, ZENG Jun, et al. Aerodynamic Effect of Turbine Blade Trailing Edge Ejection on Turbine Cascade[J]. Journal of Propulsion Technology, 2007, 28(6): 641-646.)
[17] Wright Lesley M, Blake Sarah A, Dong-Ho Rhee, et al. Effect of Upstream Wake with Vortex on Turbine Blade Platform Film Cooling with Simulated Stator-Rotor Purge Flow[J]. Journal of Turbomachinery, 2009, 131(4): 1-10.
[18] Liu S, Liu G, Xu D, et al. Aerodynamic Investigation of Endwall Film-Cooling in an Axial Turbine Cascade Part I: Experimental Investigation[R]. ISABE 99-7080.
[19] 迟重然. 气冷涡轮叶片的传热设计[D]. 哈尔滨:哈尔滨工业大学, 2011.
[20] Sridhar M, Sunnam S, Goswami S, et al. CFD Aerodynamic Performance Validation of a Two-Stage High Pressure Turbine[R]. ASME GT2011-45569.
[21] Hong B, Soh T Y, Pey L P. Development of a Helicopter Blade FE Model Using MIGA Optimization[J]. AIAA Journal, 2004, 4: 1-8.(编辑:张荣莉)　　　　　　　　　　　　　*　收稿日期:2014-12-19；修订日期:2015-03-23。基金项目:国家自然科学基金委创新研究群体(51121004；51206034)。作者简介:王龙飞,男,博士生,研究领域为气冷涡轮的叶片冷却设计。E-mail: flydrgon87@163.com