进口总压不均匀性对燃气透平端壁气热特性影响的研究

推进技术 ›› 2017, Vol. 38 ›› Issue (10): 2246-2253.

进口总压不均匀性对燃气透平端壁气热特性影响的研究

王志多^1,2,王典^1,2,张文豪^1,2,王志豪^1,2,丰镇平^1,2

西安交通大学能源与动力工程学院叶轮机械研究所，陕西西安 710049; 陕西省叶轮机械及动力装备工程实验室，陕西西安 710049,西安交通大学能源与动力工程学院叶轮机械研究所，陕西西安 710049; 陕西省叶轮机械及动力装备工程实验室，陕西西安 710049,西安交通大学能源与动力工程学院叶轮机械研究所，陕西西安 710049; 陕西省叶轮机械及动力装备工程实验室，陕西西安 710049,西安交通大学能源与动力工程学院叶轮机械研究所，陕西西安 710049; 陕西省叶轮机械及动力装备工程实验室，陕西西安 710049,西安交通大学能源与动力工程学院叶轮机械研究所，陕西西安 710049; 陕西省叶轮机械及动力装备工程实验室，陕西西安 710049

发布日期:2021-08-15
作者简介:王志多，男，博士生，研究领域为燃气透平非定常流动及传热。E-mail: wangzhiduo@foxmail.com 通讯作者:丰镇平，男，博士，教授，研究领域为热机气动热力学与传热。
基金资助:
国家自然科学基金重点项目(51336007)。

Effects of Inlet Total Pressure Non-Uniformities on Aero-Thermal Performance of Gas Turbine Endwalls

Institute of Turbomachinery，School of Energy and Power Engineering，Xi’an Jiaotong University，Xi’an 710049，China; Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment，Xi’an 710049，China,Institute of Turbomachinery，School of Energy and Power Engineering，Xi’an Jiaotong University，Xi’an 710049，China; Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment，Xi’an 710049，China,Institute of Turbomachinery，School of Energy and Power Engineering，Xi’an Jiaotong University，Xi’an 710049，China; Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment，Xi’an 710049，China,Institute of Turbomachinery，School of Energy and Power Engineering，Xi’an Jiaotong University，Xi’an 710049，China; Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment，Xi’an 710049，China and Institute of Turbomachinery，School of Energy and Power Engineering，Xi’an Jiaotong University，Xi’an 710049，China; Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment，Xi’an 710049，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究非均匀进口总压引起的燃气透平内部流动特性变化对静、动叶端壁传热的影响机制，针对GE-E3透平第一级叶片在均匀、湍流边界层及航空发动机燃烧室出口实测得到的“C”型总压三种进口条件下进行了非定常数值计算。研究表明:非均匀进口总压相对均匀进口条件对静叶端壁附近流速和入口三角区传热产生了显著影响；湍流边界层总压相对均匀总压增强了前缘马蹄涡强度，从而使静、动叶端壁前缘传热系数分别增加100%和30%；“C”型总压使静叶端壁分离线下游和动叶端壁前缘局部传热系数降低；静叶内被湍流边界层总压增强的通道涡和由“C”型总压诱导产生的对转涡均会出现在动叶上下端壁附近；残余通道涡削弱了动叶端壁横向流动并使对应位置传热系数最大降低了12%，残余对转涡则增强了动叶端壁横向流动并使端壁传热系数最大增加了38%。

关键词: 燃气轮机；总压不均匀性；端壁；二次流；传热

Abstract: To investigate the effects of the variations of turbine flow patterns induced by the non-uniform inlet total pressure on turbine stator and rotor endwall heat transfer characteristics， unsteady numerical simulations were conducted using the first stage airfoils of GE-E3 turbine with three inlet total pressure profiles. The three total pressure profiles include uniform total pressure， turbulent boundary layer total pressure， and “C” type total pressure measured at an engine combustor exit. The results show that comparing with the uniform case， total pressure non-uniformities have significant impacts on the fluid velocity near stator endwall and thus the heat transfer at the entrance triangular area. The turbulent boundary layer total pressure intensifies the horse-shoe vortices and increases the stator and rotor endwall leading edge heat transfer coefficients (HTC) by 100% and 30%， respectively. While the “C” type total pressure decreases the HTC downstream of the list-off line on stator endwall and at the certain regions of rotor endwall leading edge. The passage vortices intensified by turbulent boundary layer total pressure and counter-rotating vortices induced by “C” type total pressure in the stator passage will still exist in the rotor passage near endwalls. The residual passage vortices weaken the rotor endwall cross-flow and result in maximal HTC decline of 12% at the corresponding region. Conversely， the residual counter-rotating vortices intensify the rotor endwall cross-flow and induce maximal rotor endwall HTC increment of 38%.

Key words: Gas turbine；Total pressure non-uniformity；Endwall；Secondary flow；Heat transfer

王志多,王典,张文豪,王志豪,丰镇平. 进口总压不均匀性对燃气透平端壁气热特性影响的研究[J]. 推进技术, 2017, 38(10): 2246-2253.

WANG Zhi-duo^1,2,WANG Dian^1,2,ZHANG Wen-hao^1,2,WANG Zhi-hao^1,2,FENG Zhen-ping^1,2. Effects of Inlet Total Pressure Non-Uniformities on Aero-Thermal Performance of Gas Turbine Endwalls[J]. Journal of Propulsion Technology, 2017, 38(10): 2246-2253.

参考文献

[1] Barringer M D, Thole K A, Polanka M D. Experimental Evaluation of an Inlet Profile Generator for High-Pressure Turbine Tests[J]. ASME Journal of Turbomachinery, 2007, 129(2): 382-393.
[2] Hall B F, Chana K S, Povey T. Design of a Non-Reacting Combustor Simulator with Swirl and Temperature Distortion with Experimental Validation[R]. ASME GT 2013-95499.
[3] Andreini A, Facchini B, Insinna M, et al. Hybrid RANS-LES Modeling of a Hot Streak Generator Oriented to the Study of Combustor-Turbine Interaction[R]. ASME GT 2015-42402.
[4] Hermanson K S, Thole K A. Effect of Nonuniform Inlet Conditions on Endwall Secondary Flows[J]. ASME Journal of Turbomachinery, 2002, 124(4): 623-631.
[5] Wang Z D, Wang D, Feng Z P, et al. Numerical Analysis on Effects of Inlet Pressure and Temperature Non-Uniformities on Aero-Thermal Performance of a HP Turbine[J]. International Journal of Heat and Mass Transfer, 2017, 104: 83-97.
[6] Barringer M D, Thole K A, Polanka M D. Effects of Combustor Exit Profiles on Vane Aerodynamic Loading and Heat Transfer in a High Pressure Turbine[J]. ASME Journal of Turbomachinery, 2006, 121(2).
[7] Barringer M D, Thole K A, Polanka M D. An Experimental Study of Combustor Exit Profile Shapes on Endwall Heat Transfer in High Pressure Turbine Vanes[J]. ASME Journal of Turbomachinery, 2009, 131(2).
[8] 田兴江, 常海萍, 张镜洋, 等. 基于参数化脊线的非轴对称端壁成型方法[J]. 推进技术, 2017, 36(6): 1294-1301. (TIAN Xing-jiang, CHANG Hai-ping, ZHANG Jing-yang, et al. Non-Axisymmetric Endwall Contouring Method Based on Parameterized Ridge Line[J]. Journal of Propulsion Technology, 2017, 36(6): 1294-1301.)
[9] 查小晖, 郑群, 高杰, 等. 弧形端壁造型对不带冠涡轮气动性能的影响[J]. 推进技术, 2014, 35(6): 779-787. (CHA Xiao-hui, ZHENG Qun, GAO Jie, et al. Effects of Arcing Endwall Contouring on Aerodynamic Performances of an Unshrouded Axial Turbine[J]. Journal of Propulsion Technology, 2014, 35(6): 779-787.)
[10] 刘波, 管继伟, 陈云永, 等. 用端壁造型减小涡轮叶栅二次流损失的数值研究[J]. 推进技术, 2008, 29(3): 354-359. (LIU Bo, GUAN Ji-wei, CHEN Yun-yong, et al. Numerical Investigation for Effect of Non-Axisymmetric Endwall Profiling on Secondary Flow in Turbine Cascade[J]. Journal of Propulsion Technology, 2008, 29(3): 354-359.)
[11] 何坤, 晏鑫, 李军, 等. 燃气透平叶栅端壁传热特性的数值研究[J]. 工程热物理学报, 2014, 35(8): 1503-1507.
[12] Friedrichs S. Endwall Film-Cooling in Axial Flow Turbines[D]. Cambridgeshire: University of Cambridge, 1997.
[13] Lynch S P, Sundaram N, Thole K A, et al. Heat Transfer for a Turbine Blade with Nonaxisymmetric Endwall Contouring[J]. ASME Journal of Turbomachinery, 2011, 133(1).
[14] Laveau B, Abhari R S, Crawford M E, et al. High Resolution Heat Transfer Measurements on the Stator Endwall of an Axial Turbine[R]. ASME GT 2014-26105.
[15] Radomsky R W, Thole K A. High Free-Stream Turbulence Effects on Endwall Heat Transfer for a Gas Turbine Stator Vane[J]. ASME Journal of Turbomachinery, 2000, 122(4): 699-708.
[16] Kwak J S, Han J C. Heat-Transfer Coefficient of a Turbine Blade-Tip and Near-Tip Regions[J]. AIAA Journal of Thermophysics and Heat Transfer, 2003, 17(3): 297-303.
[17] Hermanson K S, Thole K A. Effect of Nonuniform Inlet Conditions on Endwall Secondary Flows[J]. ASME Journal of Turbomachinery, 2002, 124(4): 623-631.　　　　　　　　　　　　　*　收稿日期:2017-05-15；修订日期:2017-06-12。基金项目:国家自然科学基金重点项目(51336007)。作者简介:王志多,男,博士生,研究领域为燃气透平非定常流动及传热。E-mail: wangzhiduo@foxmail.com通讯作者:丰镇平,男,博士,教授,研究领域为热机气动热力学与传热。E-mail: zpfeng@mail.xjtu.edu.cn(编辑:田佳莹)