浅槽孔气膜冷却的大涡模拟研究

doi:10.13675/j.cnki.tjjs.190244

推进技术 ›› 2020, Vol. 41 ›› Issue (4): 830-839.DOI: 10.13675/j.cnki.tjjs.190244

浅槽孔气膜冷却的大涡模拟研究

范芳苏¹，王春华¹，冯红科¹，张靖周^1,2

1.南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016;2.先进航空发动机协同创新中心，北京 100191

发布日期:2021-08-15
作者简介:范芳苏，硕士生，研究领域为强化传热传质。E-mail：745277540@qq.com
基金资助:
国家自然科学基金（51706097；U1508212）。

Large Eddy Simulation of Film Cooling from a Shallow Trench-Hole

1.Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;2.Collaborative Innovation Center of Advanced Aero-Engine,Beijing 100191,China

Published:2021-08-15

摘要/Abstract

摘要： 为了探究浅槽孔气膜冷却的强化冷却机理，针对平板浅槽型气膜孔冷却射流与主流相干作用进行大涡模拟研究，并与圆孔射流进行对比分析。研究结果表明：浅槽孔内部会形成一对循环涡旋，将冷却气向展向卷吸；浅槽孔下游会同时出现肾形涡对和反肾形涡对，反肾形涡对抑制了气膜冷却射流的抬升，改善了冷气贴壁性；与圆孔相比，浅槽孔气膜冷却射流的流场拟序结构分布更为无序，浅槽前缘未出现马蹄涡旋，射流下游也未形成串列的发卡涡；当吹风比增长到1.5时，浅槽孔在低频区（400Hz处）出现主频，在高频区的振幅则远低于圆孔，表明高吹风比下浅槽孔气膜冷却射流流场中低频小尺度涡旋占主导作用。整体而言，浅槽孔提升了气膜的展向扩展能力，冷却性能远优于传统圆孔。

关键词: 燃气涡轮发动机;气膜冷却;射流;孔形;大涡模拟;边界层;冷却效率

Abstract: Large eddy simulation（LES）was used to study on the interaction of the mainstream and secondary flow from the hole embedded in a shallow trench on a flat plate, which was compared with the cylindrical hole to reveal the enhanced heat transfer mechanism of film cooling from the shallow trench. The results show that circular vortex pair will be formed inside the shallow trench, leading to the entrainment of coolant gas toward the spanwise direction. The kidney vortex pair and the anti-kidney vortex pair will appear at the same time. The anti-kidney vortex pair suppress the uplift of the jet flow to improve its attachment. Compared with the round hole, the distribution of coherent structure in trench configuration jet flow fluid is more disorder. The horseshoe vortex does not appear on the leading edge of the shallow cavity, and the series of hairpin vortex are not formed downstream. When the blowing ratio rises to 1.5, the dominant frequency appears in low frequency region (at 400Hz) in the flow field after the shallow trench. The pressure pulsation signal oscillates stronger than cylindrical hole, while the amplitude in the high frequency region is much lower than round hole. The results indicate that small scale vortex with low frequency dominates the film jet flow field of trench hole. Overall, the shallow trench enhances the spanwise expansion of the film, and its cooling performance is much better than that of the traditional round hole.

Key words: Gas turbine engine;Film cooling;Jet flow;Shaped hole;Large eddy simulation;Boundary layer;Cooling effectiveness

范芳苏，王春华，冯红科，张靖周. 浅槽孔气膜冷却的大涡模拟研究[J]. 推进技术, 2020, 41(4): 830-839.

FAN Fang-su¹, WANG Chun-hua¹, FENG Hong-ke¹, ZHANG Jing-zhou^1,2. Large Eddy Simulation of Film Cooling from a Shallow Trench-Hole[J]. Journal of Propulsion Technology, 2020, 41(4): 830-839.

参考文献

[1] 姚玉, 张靖周，何飞，等. 涡轮叶片吸力面气膜冷却效率的数值研究[J]. 航空动力学报， 2010， 25(6): 1245-1250.
[2] Bunker R S. Gas Turbine Heat Transfer: Ten Remaining Hot Gas Path Challenges[J]. ASME Journal of Turbomachinery， 2007， 129: 193-210.
[3] Gritsch M， Schulz A， Wittig S. Adiabatic Wall Effectiveness Measurements of Film-Cooling Holes with Expanded Exits[J]. Journal of Turbomachinery， 1998， 120:549-556.
[4] 朱惠人，许都纯，刘松龄，等. 锥形排孔气膜冷却实验研究[J]. 推进技术， 1998， 19（3）: 65-69.
[5] Sargison J E， Guo S M， Oldfield M L G， et al. A Converging Slot-Hole Film-Cooling Geometry， Part 1: Low-Speed Flat-Plate Heat Transfer and Loss[J]. Journal of Turbomachinery， 2002， 124: 453-460.
[6] Bunker R S. Film Cooling Effectiveness Due to Discrete Holes Within a Transverse Surface Slot[R]. ASME GT 2002-30178.
[7] 蒋永健，何立明，于锦禄，等. 利用横向槽改善气膜冷却效率的数值研究[J]. 推进技术， 2008， 29(3): 286-289.
[8] 章大海，陈秋炀，曾敏，等. 不同横槽结构对气膜冷却效率影响的数值研究[J]. 航空动力学报， 2008， 24(4): 611-616.
[9] Waye S， Bogard D. High Resolution of Film Cooling Effectiveness Measurements of Axial Holes Embedded in a Transverse Trench with Various Trench Configurations[R]. ASME GT 2006-90226.
[10] Lu Y， Dhungel A， Ekkad S V， et al. Effect of Trench Width and Depth on Film Cooling from Cylindrical Holes Embedded in Trenches[J]. Journal of Turbomachinery， 2009， 131(1).
[11] 戴萍，林枫. 横向槽结构对气膜冷却效果影响的数值研究[J]. 推进技术， 2011， 32(2): 253-260.
[12] Wang T， Chin T S， Bunker R S， et al. Jet Mixing in a Slot[J]. Experimental Thermal and Fluid Science， 2000， 22(1): 1-17.
[13] An B T， Liu J J， Zhang X D， et al. Film Cooling Effectiveness Measurements of a near Surface Streamwise Diffusion Hole[J]. International Journal of Heat and Mass Transfer， 2016， 103(1): 1-13.
[14] 李广超，陈钰恺，刘永泉，等. 利用W型槽提高气膜冷却效率机理[J]. 推进技术， 2016， 37(3): 520-526.
[15] Yuan L L， Street R， Ferziger J H. Large Eddy Simulation of a Round Jet in Crossflow[J]. Journal of Fluid Mechanics， 1999， 379: 71-104.
[16] Guo X， Schroder W， Meinke M. Large Eddy Simulation of Film Cooling Flows[J]. Computers & Fluids， 2006， 35(6): 587-606.
[17] Tyagi M， Acharya S. Large Eddy Simulation of Film Cooling Flow from an Inclined Cylindrical Jet[J]. Journal of Turbomachinery， 2003， 125(4): 734-742.
[18] 王扬平，姜培学. 圆孔与侧扩孔气膜冷却的大涡模拟[J]. 工程热物理学报， 2007， 28(6): 1016-1018.
[19] 吴宏，杨庆. 抑涡孔气膜冷却的大涡模拟[J]. 航空动力学报， 2012， 27(12): 2648-2654.
[20] Smagorinsky J. General Circulation Experiments with the Primitive Equations: I. The Basic Experiment[J]. Monthly Weather Review， 1963， 91: 99-164.
[21] Wang C， Zhang J， Feng H， et al. Large Eddy Simulation of Film Cooling Flow from a Fan-Shaped Hole[J]. Applied Thermal Engineering， 2018， 129: 855-870.
[22] Tyagi M， Acharya S. Large Eddy Simulation of Film Cooling Flow from an Inclined Cylindrical Jet[J]. Journal of Turbomachinery， 2003， 125(4): 734-742.
[23] Sarkar S S， Babu H. Large Eddy Simulation on the Interactions of Wake and Film Cooling near a Leading Edge[J]. Journal of Turbomachinery， 2015， 137(1).
[24] Kim S I， Hassan I. Unsteady Simulations of a Film Cooling Flow from an Inclined Cylindrical Jet[J]. Journal of Thermophysics and Heat Transfer， 2010， 24(1): 145-156.

浅槽孔气膜冷却的大涡模拟研究

Large Eddy Simulation of Film Cooling from a Shallow Trench-Hole

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价