1+1对转涡轮变工况性能分析与优化设计

推进技术 ›› 2017, Vol. 38 ›› Issue (7): 1483-1490.

1+1对转涡轮变工况性能分析与优化设计

常骐越^1,3,赵巍^1,2,雒伟伟¹,唐菲¹

中国科学院工程热物理研究所，北京 100190; 中国科学院大学，北京 100190,中国科学院工程热物理研究所，北京 100190; 中国科学院轻型动力重点实验室，北京 100190,中国科学院工程热物理研究所，北京 100190,中国科学院工程热物理研究所，北京 100190

发布日期:2021-08-15
作者简介:常骐越，男，硕士生，研究领域为叶轮机械气动热力学。
基金资助:
国家自然科学基金(51406195)；国家科技支撑计划资助(2012BAA11B01)。

Aerodynamic Performance Analysis and Improvement of a Counter-Rotating Turbine at Off-Design Conditions

Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China; University of Chinese Academy of Sciences，Beijing 100190，China,Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China; Key Laboratory of Light-Duty Gas-Turbine，Chinese Academy of Sciences，Beijing 100190，China,Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China and Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China

Published:2021-08-15

摘要/Abstract

摘要： 为阐明1+1对转涡轮变工况性能损失的主要来源并提出改进方法，以1+1对转涡轮为例进行了部分载荷工况下的流场模拟、分析和优化。与相同设计参数的同转涡轮进行部分载荷工况流场对比，发现部分转速下同转涡轮在级间导叶吸力面前缘出现分离，而1+1对转涡轮在压力面前缘出现分离。针对此流动损失，为1+1对转涡轮级间导叶提出了一种基于分离角的压力面优化设计方法，提高了近前缘压力面的气流速度，增强了其对负攻角的适应性，基本消除了叶片14%、58%和92%叶高处压力面前缘的流动分离，在正攻角工况下亦保持了良好气动性能。数值验证了该涡轮的效率在全工况范围内明显提高，而设计点效率未受负面影响。其中，在对转涡轮70%和50%设计转速的两个工况点上，低压涡轮效率较优化前分别提升了1.5%和2.0%，涡轮总效率较优化前分别提升了0.5%和0.7%。

关键词: 1+1对转涡轮；变工况；优化设计

Abstract: In order to illustrate the loss sources and enhance the aerodynamic performance of 1+1 counter-rotating turbines at off-design conditions，flow field analysis and blade profile improving method were presented through detailed numerical simulations. First，the comparison between the partly loaded flow fields of a counter-rotating turbine and a conventional two stage co-rotating turbine，which have the same design parameters，is implemented. It is found that，the boundary layer of the second vane in the co-rotating turbine separates on the suction side near the leading edge，whereas that in the counter-rotating turbine on the pressure side. Second，aiming at reducing the flow loss，a profile improving method for the pressure side of the second vane in this counter-rotating turbine is proposed，based on a theory of separation angle. This method helps to accelerate the flow on the pressure side near the leading edge and makes the second vane more adaptable to negative incidences. The redesigned vane significantly eliminates the flow separation on the pressure side near the leading edge at 14%，58% and 92% spans，and maintains a decent aerodynamic performance at positive incidence conditions. Finally，the simulation results show that the efficiencies at off-design conditions all increased and the efficiency at the design condition does not deteriorate. When the counter-rotating turbine runs at 70% and 50% design speed，the efficiencies of the low pressure stage are improved by 1.5% and 2.0%，respectively. Correspondingly，the efficiencies of the counter-rotating turbine at these two partly loaded conditions rise by 0.5% and 0.7%，respectively.

Key words: Counter-rotating turbine；Off-design conditions；Aerodynamic optimization

常骐越,赵巍,雒伟伟,唐菲. 1+1对转涡轮变工况性能分析与优化设计[J]. 推进技术, 2017, 38(7): 1483-1490.

CHANG Qi-yue^1,3,ZHAO Wei^1,2,LUO Wei-wei¹,TANG Fei¹. Aerodynamic Performance Analysis and Improvement of a Counter-Rotating Turbine at Off-Design Conditions[J]. Journal of Propulsion Technology, 2017, 38(7): 1483-1490.

参考文献

[1] Cai R. Basic Analysis of Counter-Rotating Turbines[J].International Journal of Turbo and Jet Engines, 1990, 9(1): 1-10.
[2] Arnold G A. Contrarotating Axial Flow High and Low Pressure Turbine and Compressor with Bladed Duct with Turbine Cooling[P]. US: 2477798, 1949-08-02.
[3] Wintucky W T, Stewart W L. Analysis of Two-Stage Counter-Rotating Turbine Efficiencies in Terms of Work and Speed Requirements[R]. NACA-RM-E57L05, 1957.
[4] Louis J F. Axial Flow Contra-Rotating Turbines[R]. ASME 85-GT-218.
[5] David H Silvern, William R Slivka. Analytical Investigation of Turbines with Adjustable Stator Blades and Effect of These Turbines on Jet-Engine Performance[R]. NACA-RM-E50E05, 1950.
[6] Carl E Campbell, Henry J Welna. Preliminary Evaluation of Turbine Performance with Variable-Area Turbine Nozzles in a Turbojet Engine[R]. NACA-RM-E52J20, 1952.
[7] Johnson J E. Variable Cycle Engine Developments at General Electric-1955～1995[R]. AIAA 97-15033.
[8] Benner M W, Sjolander S A, Moustapha S H. Influence of Leading-Edge Geometry on Profile Losses in Turbines at Off-Design Incidence:Experimental Results and an Improved Correlation[J]. Journal of Turbomachinery, 1997, 119(2): 193-200.
[9] Diego Torre, Raul Vazquez, Leyre Armananzas. The Effect of Airfoil Thickness on the Efficiency of Low-Pressure Turbines[J]. Journal of Turbomachinery, 2014, 136(5): 51-62.
[10] Brear M J, Hodson H P, Harvey N W. Pressure Surface Separations in Low-Pressure Turbines, Part 1:Midspan Behavior[J]. Journal of Turbomachinery, 2002, 124(3): 393-401.
[11] 刘火星, 蒋浩康, 陈懋章. 压气机叶片前缘分离流动[J]. 工程热物理学报, 2005, 25(6): 936-939.
[12] 陆宏志, 徐力平. 压气机叶片的带平台圆弧形前缘[J]. 推进技术, 2004, 24(6): 532-536. (LU Hong-zhi, XU Li-ping. Circular Leading Edge with a Flat for Compressor Blades[J]. Journal of Propulsion Technology, 2004, 24(6): 532-536.)
[13] 季路成. 对转叶轮机技术挑战分析[J]. 推进技术, 2007, 28(1): 40-44. (JI Lu-cheng. Analysis for Technique Challenges on Counter-Rotating Turbomachinery[J]. Journal of Propulsion Technology, 2007, 28(1): 40-44.)
[14] 赵庆军, 王会社, 赵晓路, 等. 涡轮转速对无导叶对转涡轮流动特性的影响[J]. 工程热物理学报, 2007, 28(6): 925-928.
[15] 张惠, 王会社, 唐菲, 等. 非设计工况下 1+ 1/2 对转涡轮性能研究[J]. 工程热物理学报, 2007, 28(4): 571-573.
[16] Zhao W, Wu B, Xu J. Aerodynamic Design and Analysis of a Multistage Vaneless Counter-Rotating Turbine[J]. Journal of Turbomachinery, 2015, 137(6): 303-312.
[17] O’Meara M M, Mueller T J. Laminar Separation Bubble Characteristics on an Airfoil at Low Reynolds Numbers[J]. AIAA Journal, 1987, 25(8): 1033-1041.
[18] 童秉纲, 孔祥言, 邓国华. 气体动力学[M]. 北京:高等教育出版社, 1990.(编辑:张荣莉)　　　　　　　　　　　　　　收稿日期:2016-03-03；修订日期:2016-05-03。基金项目:国家自然科学基金(51406195)；国家科技支撑计划资助(2012BAA11B01)。作者简介:常骐越,男,硕士生,研究领域为叶轮机械气动热力学。E-mail: changqiyue@iet.cn