Study on Effects of Film Hole Arrangements on Film Cooling and Aerodynamic Characteristics of Turbine Endwall

doi:10.7652/xjtuxb202308003

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Study on Effects of Film Hole Arrangements on Film Cooling and Aerodynamic Characteristics of Turbine Endwall

更新时间：2025-05-08

- Study on Effects of Film Hole Arrangements on Film Cooling and Aerodynamic Characteristics of Turbine Endwall
- Vol. 57, Issue 8, Pages: 22-33(2023)
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202308003
  CLC： TK474.7
- Online First：10 August 2023，
  
  Published：2023
- 稿件说明：
移动端阅览
Study on Effects of Film Hole Arrangements on Film Cooling and Aerodynamic Characteristics of Turbine Endwall[J]. 2023, 57(8): 22-33.
DOI：

Study on Effects of Film Hole Arrangements on Film Cooling and Aerodynamic Characteristics of Turbine Endwall[J]. 2023, 57(8): 22-33. DOI： 10.7652/xjtuxb202308003.

摘要

为了研究燃机透平端壁气膜冷却特性

对存在装配间隙泄漏流条件下端壁不同气膜孔布置的气膜冷却进行了分析。采用压敏漆技术对端壁气膜冷却效率进行了测量

并利用实验结果对湍流模型进行了校核; 对所研究模型的网格无关性进行了验证

在此基础上

采用实验给定的边界条件

研究了存在装配间隙泄漏流的端壁在不同气膜孔布置下的气膜冷却特性及气动损失特性

详细分析了5种冷气吹风比(M=0.5

1.0

1.5

2.0

2.5)和4种气膜孔布置下端壁气膜冷却特性和气动特性。结果表明:对于气膜孔布置A(S=0.065C

=-56.6°

S为第二组气膜孔到装配间隙的距离

为叶片轴向弦长

为第二组气膜孔复合角)

吹风比为0.5时

端壁气膜冷却效率最大

随着吹风比的增大

气膜孔出口冷气脱离端壁表面

气膜孔周围的气膜冷却效率下降; 4种不同气膜孔布置下叶栅出口处近端壁区域的总压损失系数均随着吹风比的增大而降低

其中气膜孔布置A的降低幅度最大; 低吹风比(M=0.5)时

气膜孔布置对端壁气膜冷却特性影响较小; 高吹风比(M=2.5)时

气膜孔布置D(S=0.1C

=30°)端壁气膜冷却效率最高。

Abstract

A numerical study was carried out for the effects of different film hole arrangements on film cooling characteristics of turbine endwall with mid-passage gap leakage. Firstly

the film cooling effectiveness of a gas turbine endwall was measured with PSP method

and the results was adopted for turbulence model validation. Then mesh independence analysis was carried out for the model under study. On this basis

the film cooli

ng and aerodynamic loss characteristics under different film hole arrangements of the endwall with mid-passage gap leakage were studied. The film cooling and aerodynamic characteristics under five different blowing ratios(M=0.5

1.0

1.5

2.0

2.5)and four film hole arrangements were analyzed in detail. Results show that when the blowing ratio is 0.5

the endwall film cooling effectiveness reaches its maximum value under arrangement A(S=0.065C

=-56.6°; S is the distance between second group film holes and mid-passage gap

is the axial chord length of the blade

and γ

is the compound angles of the second group film holes). With the increase of blowing ratio

the film coolant jets off from the endwall surface

and the film cooling effectiveness near the film hole decreases. Under the four different film hole arrangements

the total pressure loss coefficient in the near wall area decreases with the increase of the blowing ratio. The decrease amplitude under arrangement A is the greatest. The film hole arrangement has little effect on the endwall film cooling under a low blowing ratio(M=0.5). The film cooling effectiveness(S=0.1C

=30°)is the highest under arrangement D and a high blowing ratio(M=2.5).

关键词

Keywords

references

SHARMA O P, BUTLER T L. Predictions of endwall losses and secondary flows in axial flow turbine cascades [J]. Journal of Turbomachinery, 1987, 109(2): 229-238

SIEVERDING C H, VAN DEN BOSCHE P. The use of coloured smoke to visualize secondary flows in a turbine-blade cascade [J]. Journal of Fluid Mechanics, 1983, 134: 85-89

ALQEFL M H, NAWATHE K P, CHEN Pingting, et al. Aero-thermal aspects of film cooled nozzle guide vane endwall: part 2 thermal measurements [J]. Journal of Turbomachinery, 2021, 143(12): 121010

刘高文, 刘松龄, 朱惠人, 等. 涡轮叶栅前缘上游端壁气膜冷却的传热实验研究 [J]. 航空动力学报, 2001, 16(3): 249-255.LIU Gaowen, LIU Songling, ZHU Huiren, et al. Endwall heat transfer and film cooling measurements in a turbine cascade with injection upstream of leading edge [J]. Journal of Aerospace Power, 2001, 16(3): 249-255

THRIFT A A, THOLE K A, HADA S. Effects of orientation and position of the combustor-turbine interface on the cooling of a vane endwall [C]//ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. New York, NY, USA: ASME, 2011: 291-301

PIGGUSH J D, SIMON T W. Flow measurements in a first stage nozzle cascade having endwall contouring, leakage, and assembly features [J]. Journal of Turbomachinery, 2013, 135(1): 011002

张杰, 刘存良, 张丽, 等. 槽缝射流和泄漏间隙对轴对称涡轮端壁换热特性的影响 [J]. 推进技术, 2022, 43(4): 195-203.ZHANG Jie, LIU Cunliang, ZHANG Li, et al. Effects of slot injection and leakage gap on heat transfer characteristics of an axisymmetric turbine endwall [J]. Journal of Propulsion Technology, 2022, 43(4): 195-203

叶创捷, 潘丞雄, 张玫宝, 等. 动叶端壁离散孔气膜冷却的数值研究 [J]. 热能动力工程, 2019, 34(5): 28-36.YE Chuangjie, PAN Chengxiong, ZHANG Meibao, et al. Computation study of discrete hole film cooling on turbine rotor endwall [J]. Journal of Engineering for Thermal Energy and Power, 2019, 34(5): 28-36

叶创捷. 端壁传热与气膜冷却的实验研究 [J]. 能源工程, 2019(3): 27-34.YE Chuangjie. Experimental study of the heat transfer and film cooling on rotor endwall [J]. Energy Engineering, 2019(3): 27-34

祝培源, 陶志, 姚韵嘉, 等. 槽缝射流对环形叶栅端壁气膜冷却性能影响的实验研究 [J]. 西安交通大学学报, 2019, 53(11): 63-70.ZHU Peiyuan, TAO Zhi, YAO Yunjia, et al. Experimental study on the effect of purge flow on film cooling performance of an annular cascade endwall [J]. Journal of Xi'an Jiaotong University, 2019, 53(11): 63-70

姚韵嘉, 祝培源, 陶志, 等. 间隙射流对端壁气膜冷却性能影响的实验研究 [J]. 西安交通大学学报, 2019, 53(3): 43-49, 55.YAO Yunjia, ZHU Peiyuan, TAO Zhi, et al. Experimental study on the effect of gap jet on film cooling performance of endwall [J]. Journal of Xi'an Jiaotong University, 2019, 53(3): 43-49, 55

CARDWELL N D, SUNDARAM N, THOLE K A. The effects of varying the combustor-turbine gap [J]. Journal of Turbomachinery, 2007, 129(4): 756-764

杨星, 刘钊, 刘战胜, 等. 端壁通道间隙对端壁泄漏流冷却的影响 [J]. 工程热物理学报, 2017, 38(1): 44-48.YANG Xing, LIU Zhao, LIU Zhansheng, et al. Effects of mid-passage gap on endwall purge flow film cooling [J]. Journal of Engineering Thermophysics, 2017, 38(1): 44-48

杨星, 刘钊, 刘战胜, 等. 端壁错位对端壁泄漏流冷却的影响研究 [J]. 工程热物理学报, 2017, 38(4): 719-725.YANG Xing, LIU Zhao, LIU Zhansheng, et al. Effects of endwall misalignment on endwall purge flow film cooling [J]. Journal of Engineering Thermophysics, 2017, 38(4): 719-725

PARK S, KIM J J, BANG M, et al. Effects of seal installation in the mid-passage gap between turbine blade platforms on film cooling [J]. Applied Thermal Engineering, 2021, 189: 116683

ZHANG Kaiyuan, LI Jun, LI Zhigang, et al. Effects of simulated swirl purge flow and mid-passage gap leakage on turbine blade platform cooling and suction surface phantom cooling performance [J]. International Journal of Heat and Mass Transfer, 2019, 129: 618-634

RODRIGUEZ S. Effect of pressure gradient and wake on endwall film cooling effectiveness [D]. Orlando, FL, USA: University of Central Florida, 2008

COLBAN W, THOLE K. Influence of hole shape on the performance of a turbine vane endwall film-cooling scheme [J]. International Journal of Heat and Fluid Flow, 2007, 28(3): 341-356

ZHANG Luzeng, YIN Juan, LIU K, et al. Effect of hole diameter on nozzle endwall film cooling and associated phantom cooling [C]//ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. New York, NY, USA: ASME, 2015: V05BT12A016

DU Kun, SONG Liming, LI Jun, et al. Effects of the layout of film holes near the vane leading edge on the endwall cooling and phantom cooling of the vane suction side surface [J]. Numerical Heat Transfer: Part A Applications, 2017, 71(9): 910-927

MILIDONIS K F, GEORGIOU D P. Film cooling effectiveness predictions in the region of the blade-endwall junction corner with injection assisted by the recirculating vortex flow [J]. Progress in Computational Fluid Dynamics, an International Journal, 2018, 18(6): 362-375

SHIAU C C, SAHIN I, ULLAH I, et al. Transonic turbine vane endwall film cooling using the pressure-sensitive paint measurement technique [J]. Journal of Turbomachinery, 2020, 142(8): 081004

袁瑞明. 大温比下端壁气膜冷却与气膜孔-涡发生器组合冷却的实验研究 [D]. 合肥: 中国科学技术大学, 2017

张扬, 李毅飞, 袁新. 进口旋流对透平双通道叶栅端壁气膜冷却的影响 [J]. 工程热物理学报, 2017, 38(1): 81-86.ZHANG Yang, LI Yifei, YUAN Xin. Effects of inlet rotating flow on endwall film cooling [J]. Journal of Engineering Thermophysics, 2017, 38(1): 81-86

王晓春, 苏杭, 李娟, 等. 温度比对导叶端壁冷却特性的影响 [J]. 航空动力学报, 2019, 34(6): 1344-1351.WANG Xiaochun, SU Hang, LI Juan, et al. Effect of temperature ratio on cooling characteristics of vane end-wall [J]. Journal of Aerospace Power, 2019, 34(6): 1344-1351

白波, 李志刚, 李军. 上游台阶结构对跨声速透平叶栅端壁气膜冷却性能的影响 [J]. 西安交通大学学报, 2020, 54(5): 1-8.BAI Bo, LI Zhigang, LI Jun. Investigation on the effect of upstream step geometry on endwall film cooling characteristics of a transonic turbine cascade [J]. Journal of Xi'an Jiaotong University, 2020, 54(5): 1-8

白波, 李志刚, 李军. 轴向收敛造型对燃气涡轮叶栅端壁气膜冷却性能的影响 [J]. 航空动力学报, 2022, 37(5): 1042-1053.BAI Bo, LI Zhigang, LI Jun. Influence of axially-convergent contouring on cascade endwall film cooling characteristics in gas turbine [J]. Journal of Aerospace Power, 2022, 37(5): 1042-1053

张韦馨, 刘战胜, 杨星, 等. 射流角和质量流量比对涡轮端壁气膜冷却特性的影响 [J]. 西安交通大学学报, 2021, 55(4): 107-115.ZHANG Weixin, LIU Zhansheng, YANG Xing, et al. Effects of mass flow ratio and film hole orientation angle on turbine endwall film cooling characteristics [J]. Journal of Xi'an Jiaotong University, 2021, 55(4): 107-115

LI Feng, LIU Zhao, FENG Zhenping. Film cooling and aerodynamic performance on multi-cavity squealer tip of a turbine blade [C]//ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. New York, NY, USA: ASME, 2021: V05AT12A025.

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