| Citation: | ZHANG Shen, LI Guoqing, LIU Hao, et al. Multi region compound angle film cooling characteristics on pressure side of turbine guide vane[J]. Journal of Aerospace Power, 2024, 39（3）：20220177 doi: 10.13224/j.cnki.jasp.20220177
|
In view of the phenomenon that the secondary flow in the channel causes the deflection of the film trajectory on the pressure surface, the concept of multi region compound angle along the spanwise direction was proposed. Numerical simulation was conducted to investigate the film cooling characteristics of turbine guide vane HS1A. The influences of secondary flow, compound angle and blowing ratio on the film cooling characteristics were analyzed under the condition of turbine outlet Reynolds number of 2.3×105. The results showed that the secondary flow in the near endwall had the ability to promote the spanwise coverage of the film, which improved the cooling effectiveness downstream the film hole outlet compared with the mid blade region, but also intensified the mixing of the jet and the mainstream, and reduced the effective coverage length of the film; according to the secondary flow in different spanwise regions, the film hole compound angle in each region was finely arranged, which can correct all the deflection angles of the film trajectory to 0°, and the average film cooling effectiveness was increased by 10.42%; the compound angle cooling model had good applicability within the range of blowing ratio of 0.5−1.0. When the blowing ratio increased to 1.3, the film trajectory could deflect reversely.
| [1] |
PEREPEZKO J H. The hotter the engine,the better[J]. Science,2009,326(5956): 1068-1069. doi: 10.1126/science.1179327
|
| [2] |
HAN J C,DUTTA S,EKKAD S. Gas turbine heat transfer and cooling technology[M]. New York,US: Taylor & Francis,2001.
|
| [3] |
ANDREOPOULOS J. On the structure of jets in a crossflow[J]. Journal of Fluid Mechanics,1985,157: 163-197. doi: 10.1017/S0022112085002348
|
| [4] |
BALDAUF S,SCHULZ A,WITTIG S. High-resolution measurements of local heat transfer coefficients from discrete hole film cooling[J]. Journal of Turbomachinery,2001,123(4): 749-757. doi: 10.1115/1.1387245
|
| [5] |
侯亚东,单勇,李江宁,等. 各向异性复合材料平板气膜冷却特性实验和数值研究[J]. 航空动力学报,2017,32(10): 2384-2393. HOU Yadong,SHAN Yong,LI Jiangning,et al. Experimental and numerical studies on the film cooling characteristics of anisotropic composite plates[J]. Journal of Aerospace Power,2017,32(10): 2384-2393. (in Chinese
|
| [6] |
韦宏,祖迎庆. 基于真实密度比的单/三排扇形孔气膜冷却性能及流阻特性[J]. 航空动力学报,2021,36(11): 2331-2343. WEI Hong,ZU Yingqing. Film cooling performance and flow resistance characteristics of single/triple-row fan-shaped holes based on actual density ratio[J]. Journal of Aerospace Power,2021,36(11): 2331-2343. (in Chinese
|
| [7] |
GRITSCH M,SCHULZ A,WITTIG S. Effect of internal coolant crossflow on the effectiveness of shaped film-cooling holes[J]. Journal of Turbomachinery,2003,125(3): 547-554. doi: 10.1115/1.1580523
|
| [8] |
张盛昌,张靖周,谭晓茗. 利用上游沙丘形斜坡增强气膜冷却[J]. 航空动力学报,2020,35(5): 973-982. ZHANG Shengchang,ZHANG Jingzhou,TAN Xiaoming. Film cooling enhancement by using upstream sand-dune-shaped ramp[J]. Journal of Aerospace Power,2020,35(5): 973-982. (in Chinese
|
| [9] |
孟通,朱惠人,刘存良,等. 边倒圆型气膜孔流动换热特性研究[J]. 推进技术,2018,39(5): 1067-1076. MENG Tong,ZHU Huiren,LIU Cunliang,et al. Experimental and numerical study on film cooling performance of radiusing-type hole[J]. Journal of Propulsion Technology,2018,39(5): 1067-1076. (in Chinese
|
| [10] |
BERHE M K,PATANKAR S V. Curvature effects on discrete-hole film cooling[J]. Journal of Turbomachinery,1999,121(4): 781-791. doi: 10.1115/1.2836732
|
| [11] |
LIGRANI P M,WIGLE J M,JACKSON S W. Film-cooling from holes with compound angle orientations: Part 2 results downstream of a single row of holes with 6d spanwise spacing[J]. Journal of Heat Transfer,1994,116(2): 353-362. doi: 10.1115/1.2911407
|
| [12] |
WANG Xian,SHANGGUAN Yanqin,ZHANG Hu,et al. Numerical study on the near-wall characteristics of compound angled film cooling based on hybrid thermal lattice Boltzmann method[J]. Applied Thermal Engineering,2018,129: 1670-1681. doi: 10.1016/j.applthermaleng.2017.10.125
|
| [13] |
王建明,刘炜,徐志晖,等. 文氏效应在叶片根部马蹄涡控制中的应用[J]. 航空动力学报,2011,26(11): 2617-2622. WANG Jianming,LIU Wei,XU Zhihui,et al. Study on the control of the wing-body juncture horseshoe vortex utilizing Venturi tube[J]. Journal of Aerospace Power,2011,26(11): 2617-2622. (in Chinese doi: 10.13224/j.cnki.jasp.2011.11.002
|
| [14] |
贾希诚,王正明. 叶轮机械中间隙流与通道二次流相互作用的数值研究[J]. 航空动力学报,2002,17(4): 399-403. JIA Xicheng,WANG Zhengming. Numerical study of interaction between clearance flow and passage secondary flow in turbomachinery[J]. Journal of Aerospace Power,2002,17(4): 399-403. (in Chinese doi: 10.13224/j.cnki.jasp.2002.04.003
|
| [15] |
GAO Zhihong,NARZARY D P,HAN J C. Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes[J]. International Journal of Heat and Mass Transfer,2008,51(9/10): 2139-2152.
|
| [16] |
GAO Zhihong,NARZARY D P,HAN J C. Film-cooling on a gas turbine blade pressure side or suction side with compound angle shaped holes[J]. Journal of Turbomachinery,2009,131(1): 011019. doi: 10.1115/1.2813012
|
| [17] |
NARZARY D P,LIU Kuochun,RALLABANDI A P,et al. Influence of coolant density on turbine blade film-cooling using pressure sensitive paint technique[J]. Journal of Turbomachinery,2012,134(3): 031006. doi: 10.1115/1.4003025
|
| [18] |
ZHOU Zhiyu,LI Haiwang,XIE Gang,et al. The cooling performance of three-row compound angle holes on the suction surface of a rotating turbine blade[J]. Propulsion and Power Research,2021,10(1): 23-36. doi: 10.1016/j.jppr.2020.09.001
|
| [19] |
CORRIVEAU D. Influence of loading distribution on the performance of high pressure turbine blades[D]. Ottawa,Canada: Carleton University,2005.
|
DownLoad:
