| Citation: | FU Zhongyi, DU Yingjie, YE Wei, et al. Effect of combustor exit swirl on film cooling characteristics of shaped holes on the pressure surface of high-pressure turbine vanes[J]. Journal of Aerospace Power, 2026, 41（3）：20240828 doi: 10.13224/j.cnki.jasp.20240828
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To elucidate the impact mechanism of swirl characteristics at the combustor exit on the film cooling performance of shaped film cooling holes on the pressure surface of high-pressure turbine vanes, particle image velocimetry (PIV) technology was employed in conjunction with numerical simulations to analyze the distribution characteristics of the strong swirl flow field at the combustor exit under a constant mainstream inlet Reynolds number ($ Re $). Subsequently, numerical simulations were conducted to compare and analyze the effects of swirl inflow on the flow characteristics of the pressure surface of curved and twisted turbine vanes and the film cooling characteristics of single-row cylindrical holes, fan-shaped holes, laid-back holes, and laid-back fan-shaped holes. The results indicated that strong swirl intake induced a significant radial pressure gradient on the pressure surface, causing the film cooling trajectories to radially deflect and converge to localized areas. This led to decreased cooling efficiency and increased non-uniformity of the cooling distribution. When the mainstream inlet $ Re $ remained constant, increasing the blowing ratio (
| [1] |
李军, 栗智宇, 李志刚, 等. 燃烧室和涡轮相互作用下高压涡轮级气热性能研究进展[J]. 航空学报, 2021, 42(3): 024111. LI Jun, LI Zhiyu, LI Zhigang, et al. Aerothermal performance of high pressure turbine stage with combustor-turbine interactions: Review[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(3): 024111. (in Chinese
LI Jun, LI Zhiyu, LI Zhigang, et al. Aerothermal performance of high pressure turbine stage with combustor-turbine interactions: Review[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(3): 024111. (in Chinese)
|
| [2] |
XIN Qiurui, BAI Xiaohui, JIN Helong, et al. Comprehensive study on cooling effectiveness and thermoelectric conversion of a novel helium/hydrogen-based closed Brayton cooling system for a hydrogen aero-engine[J]. Case Studies in Thermal Engineering, 2025, 67: 105741. doi: 10.1016/j.csite.2025.105741
|
| [3] |
BAUER H J. New low emission strategies and combustor designs for civil aeroengine applications[J]. Progress in Computational Fluid Dynamics, an International Journal, 2004, 4(3/4/5): 130. doi: 10.1504/PCFD.2004.004081
|
| [4] |
靳合龙, 白晓辉, 张振华, 等. 不同开度可调涡轮导叶前缘气膜冷却效果研究[J]. 燃气涡轮试验与研究, 2024, 37(2): 19-28. JIN Helong, BAI Xiaohui, ZHANG Zhenhua, et al. Leading edge film cooling effectiveness of variable turbine guide vane with different opening degrees[J]. Gas Turbine Experiment and Research, 2024, 37(2): 19-28. (in Chinese doi: 10.3724/j.GTER.20240017
JIN Helong, BAI Xiaohui, ZHANG Zhenhua, et al. Leading edge film cooling effectiveness of variable turbine guide vane with different opening degrees[J]. Gas Turbine Experiment and Research, 2024, 37(2): 19-28. (in Chinese) doi: 10.3724/j.GTER.20240017
|
| [5] |
BAI Xiaohui, JIN Helong, DU Yingjie, et al. Theoretical study on showerhead film cooling effectiveness of adjustable guide vane installation angle for variable cycle Aeroengine[J]. International Journal of Thermal Sciences, 2025, 212: 109786. doi: 10.1016/j.ijthermalsci.2025.109786
|
| [6] |
QURESHI I, SMITH A D, POVEY T. HP vane aerodynamics and heat transfer in the presence of aggressive inlet swirl[J]. Journal of Turbomachinery, 2013, 135(2): 021040. doi: 10.1115/1.4006610
|
| [7] |
HALL B F, CHANA K S, POVEY T. Design of a nonreacting combustor simulator with swirl and temperature distortion with experimental validation[J]. Journal of Engineering for Gas Turbines and Power, 2014, 136(8): 081501. doi: 10.1115/1.4026809
|
| [8] |
QURESHI I, POVEY T. A combustor-representative swirl simulator for a transonic turbine research facility[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2011, 225(7): 737-748. doi: 10.1177/0954410011400817
|
| [9] |
SCHMID G, KRICHBAUM A, WERSCHNIK H, et al. The impact of realistic inlet swirl in a 1 ½ stage axial turbine[R]. ASME paper GT2014-26716, 2014.
|
| [10] |
ZHANG Wenhao, WANG Zhihao, WANG Zhiduo, et al. Study on film cooling performance improvement of NGV leading edge subject to distortion profiles of low NOx combustor[R]. ASME Paper GT2020-15975, 2020.
|
| [11] |
SALVADORI S, OTTANELLI L, JONSSON M, et al. Investigation of high-pressure turbine endwall film-cooling performance under realistic inlet conditions[J]. Journal of Propulsion and Power, 2012, 28(4): 799-810. doi: 10.2514/1.B34365
|
| [12] |
SCHNEIDER M. Robust aero-thermal design of high pressure turbines at uncertain exit conditions of low-emission combustion systems[D]. Darmstadt, Germany : Darmstadt University of Technology, 2019.
|
| [13] |
JACOBI S, MAZZONI C, ROSIC B, et al. Investigation of unsteady flow phenomena in first vane caused by combustor flow with swirl[J]. Journal of Turbomachinery, 2017, 139(4): 041006. doi: 10.1115/1.4035073
|
| [14] |
INSINNA M, GRIFFINI D, SALVADORI S, et al. On the effect of an aggressive inlet swirl profile on the aero-thermal performance of a cooled vane[J]. Energy Procedia, 2015, 81: 1113-1120. doi: 10.1016/j.egypro.2015.12.133
|
| [15] |
WANG Zhiduo, WANG Dian, WANG Zhihao, et al. Heat transfer analyses of film-cooled HP turbine vane considering effects of swirl and hot streak[J]. Applied Thermal Engineering, 2018, 142: 815-829. doi: 10.1016/j.applthermaleng.2018.07.044
|
| [16] |
BACCI T, BECCHI R, PICCHI A, et al. Adiabatic effectiveness on high-pressure turbine nozzle guide vanes under realistic swirling conditions[J]. Journal of Turbomachinery, 2019, 141(1): 011009. doi: 10.1115/1.4041559
|
| [17] |
GILLER L, SCHIFFER H P. Interactions between the combustor swirl and the high pressure stator of a turbine[R]. ASME Paper GT2012-69157, 2012.
|
| [18] |
WANG Zhihao, WANG Zhiduo, ZHANG Wenhao, et al. Numerical study on unsteady film cooling performance of turbine rotor considering influences of inlet non-uniformities and upstream coolant[J]. Aerospace Science and Technology, 2021, 119: 107089. doi: 10.1016/j.ast.2021.107089
|
| [19] |
SEO H J, KANG Y J, LEE H C, et al. Optimization of the configuration of the laidback fan-shaped film cooling hole with a lateral expansion angle of 10 degrees[J]. Applied Thermal Engineering, 2019, 153: 379-389. doi: 10.1016/j.applthermaleng.2019.03.029
|
| [20] |
ELY M J, JUBRAN B A. Film cooling from short holes with sister hole influence[R]. ASME Paper GT2012-68081, 2012.
|
| [21] |
YE Lin, GUO Hao, ZHU Yinhai, et al. Large eddy simulation of film cooling flow from diffusion slot hole with crossflow coolant configuration[J]. Physics of Fluids, 2023, 35(5): 055101. doi: 10.1063/5.0143002
|
| [22] |
江艳, 李海旺, 谢刚, 等. 高压涡轮导叶压力面异型气膜孔特性[J]. 航空动力学报, 2024, 39(11): 20220963. JIANG Yan, LI Haiwang, XIE Gang, et al. Characteristics of shaped holes on the pressure surface of turbine vane[J]. Journal of Aerospace Power, 2024, 39(11): 20220963. (in Chinese
JIANG Yan, LI Haiwang, XIE Gang, et al. Characteristics of shaped holes on the pressure surface of turbine vane[J]. Journal of Aerospace Power, 2024, 39(11): 20220963. (in Chinese)
|
| [23] |
WU Zhuang, ZHU Huiren, LIU Cunliang, et al. Showerhead film cooling injection orientation design on the turbine vane leading edge considering representative lean burn combustor outflow[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2021, 235(15): 2342-2356. doi: 10.1177/0954410021996566
|
| [24] |
WANG Xinyu, LIU Cunliang, FU Zhongyi, et al. Improvement of film cooling design for turbine vane leading edge considering combustor outflow[J]. Journal of Thermal Science, 2024, 33(1): 311-327. doi: 10.1007/s11630-023-1878-8
|
| [25] |
XU Zhipeng, LIU Cunliang, YE Lin, et al. Investigation of the effect of combustor swirl flow on turbine vane full coverage film cooling[J]. Energy, 2024, 295: 130965. doi: 10.1016/j.energy.2024.130965
|
| [26] |
HUANG Ying, YANG V. Dynamics and stability of lean-premixed swirl-stabilized combustion[J]. Progress in Energy and Combustion Science, 2009, 35(4): 293-364. doi: 10.1016/j.pecs.2009.01.002
|
| [27] |
KIM I, KIM J, CHOE Y, et al. Effect of vane angle on combustion characteristics of premixed H2/air in swirl micro-combustors with straight vane or twisted vane[J]. Applied Thermal Engineering, 2023, 228: 120528. doi: 10.1016/j.applthermaleng.2023.120528
|
| [28] |
WU Zhuang, ZHU Huiren, LIU Cunliang, et al. Superposition effect of the leading edge film on the downstream film cooling of a turbine vane under combustor swirling outflow[J]. Journal of Engineering for Gas Turbines and Power, 2022, 144(3): 031022. doi: 10.1115/1.4052989
|
| [29] |
WERSCHNIK H, HILGERT J, WILHELM M, et al. Influence of combustor swirl on endwall heat transfer and film cooling effectiveness at the large scale turbine rig[J]. Journal of Turbomachinery, 2017, 139(8): 081007. doi: 10.1115/1.4035832
|
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