缝槽入口形状对气膜冷却性能的影响

上海交通大学学报（自然版） ›› 2012, Vol. 46 ›› Issue (04): 550-555.

缝槽入口形状对气膜冷却性能的影响

万超一1, 饶琨2, 饶宇1, 许亚敏3

(1. 上海交通大学机械与动力工程学院叶轮机械研究所，上海 200240；2. 杭州大路实业有限公司，杭州 311234； 3. 上海交通大学航空航天学院，上海 200240)

收稿日期:2011-05-29 出版日期:2012-04-28 发布日期:2012-04-28
基金资助:
国家自然科学基金资助项目（50806045）

Effects of Slot Geometry on the Film Cooling Performance

WAN Chao-Yi-1, RAO Kun-2, RAO Yu-1, XU Ya-Min-3

(1. Institute of Turbomachinery, School of Mechanical Engineering, Shanghai Jiaotong Unversity, Shanghai 200240, China； 2.Hangzhou Dalu Co. Ltd., Hangzhou 311234, China； 3.School of Aeronautics & Astronautics, Shanghai Jiaotong Unversity, Shanghai 200240, China)

Received:2011-05-29 Online:2012-04-28 Published:2012-04-28

摘要/Abstract

摘要： 通过对直缝槽、渐缩型和渐扩型缝槽的气膜冷却进行数值计算分析，获得了缝槽入口形状对气膜冷却性能的影响.首先采用基于k-ω的剪应力输运湍流模型（SST）和雷诺应力输运模型（RSTM）对缝槽气膜冷却进行了计算，并与文献数据进行了比较，验证了在相同网格质量条件下SST湍流模型能更准确地模拟缝槽气膜冷却中的流动和传热特征.在此基础上，对具有45°喷射角和具有相同缝槽出口截面积的直缝槽、渐缩型和渐扩型缝槽在不同吹风比条件下的气膜冷却效率进行了比较.数值计算结果表明，缝槽的入口几何形状对气膜冷却性能有重要影响，直缝槽的气膜冷却性能优于渐缩缝槽和渐扩缝槽；根据吹风比M=4时二次流出口附近的温度场、流线图和湍流动能分布，探讨了渐缩缝槽和渐扩缝槽冷却效率降低的原因.最后给出了M=4时缝槽出口附近的静压扰动，从机理上阐述了二次流出口后部涡形成的原因.

关键词: 缝槽气膜冷却, 流动, 传热, 数值计算

Abstract: A numerical study was conducted to investigate the film cooling performance of a straight slot, a converging slot and a diffuser slot. Firstly, a shear stress transport (SST) k-ω model and a Reynolds stress turbulence model (RSTM) were respectively used to calculate the slot film cooling, and the calculation results were compared with the existing literature data. The comparison indicates that for the same mesh gird, the SST model shows a better performance in simulating the flow and heat transfer characteristics in the slot film cooling. Based on the validated model, the film cooling effectiveness of the different kinds of slot with the same jet angle (45°) as well as the same exit geometry at different blowing ratios was obtained. The results show the slot geometry plays an important role in the film cooling performance, and the straight slot has the best film cooling performance than the other two slots. The temperature field, streamline traces and the turbulent kinetic energy field around the film cooling slots at M = 4 are also obtained to analyze the underlying mechanisms of the slot geometry influencing the film cooling performance.

Key words: slot film cooling, flow, heat transfer, numerical computation

中图分类号:

TK 47

万超一1, 饶琨2, 饶宇1, 许亚敏3. 缝槽入口形状对气膜冷却性能的影响[J]. 上海交通大学学报（自然版）, 2012, 46(04): 550-555.

WAN Chao-Yi-1, RAO Kun-2, RAO Yu-1, XU Ya-Min-3. Effects of Slot Geometry on the Film Cooling Performance[J]. Journal of Shanghai Jiaotong University, 2012, 46(04): 550-555.

参考文献

［1］Nasir H, Ekkad S V, Acharya S. Effect of compound angle injection on flat surface film cooling with large streamwise injection angle［J］. Experimental Thermal and Fluid Science， 2001， 25（1）: 2329.

［2］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Transactions of the Asme, 2002,124(3): 453460.

［3］Burd S W, Satterness C J, Simon T W. Effects of slot bleed injection over a contoured end wall on nozzle guide vane cooling performance. Part II:Thermal measurements［C］// Proceedings of the ASME Turbo Expo 2000. USA: American Society of Mechanical Engineers, 2000:200210.

［4］Oke R, Simon T, Shih T, et al. Measurements over a filmcooled contoured endwall with various coolant injection rates［C］// Proceedings of the ASME Turbo Expo 2001. USA: American Society of Mechanical Engineers, 2001: 140149.

［5］Oke R A, Simon T W. Film cooling experiments with flow introduced upstream of a first stage nozzle guide vane through slots of various geometries［C］// Proceedings of the ASME Turbo Expo 2002. USA: American Society of Mechanical Engineers, 2002: 3340.

［6］Lin Y L, Shih T I P. Film cooling of a cylindrical leading edge with injection through rows of compound angle holes［J］. Journal of Heat Transfer，2001， 123(4)： 645654.

［7］Menter F R. Twoequation eddyViscosity turbulence models for engineering applications［J］. AIAA Journal， 1994， 32(8)： 15981605.

［8］Cruse M W. A study of film cooling adiabatic effectiveness for turbine blade leading edges［D］. Texas： University of Texas at Austin, 1997.

［9］Jia R, Sundén B, Miron, P, et al. A numerical and experimental investigation of the slot filmcooling jet with various angles［J］. Journal of Turbomachinery, 2005, 127（3）: 635645.

［10］Durbin P A. Separated flow components with k-ε-ν2 model［J］. AIAA Journal, 1995,33(4): 659–664.

［11］Wilcox D C. Turbulence modeling for CFD［M］. 3rd ed .La Canada: DCW Industries Inc, 2006.

［12］Launder B E, Reece G J, Rodi W. Progress in the development of a reynoldsstress turbulence closure ［J］. Journal of Fluid Mechanics, 1975, 68(3): 537566.

［13］Chen K S, Hwang J Y. Experimental study on the mixing of oneand dualline heated jets with a cold crossflow in a confined channel［J］. AIAA Journal, 1991, 29(3): 353360.

[1]	王志伟, 何炎平, 李铭志, 仇明, 黄超, 刘亚东. 基于计算流体力学的90° 弯管气液两相流数值模拟及流型演化[J]. 上海交通大学学报, 2022, 56(9): 1159-1167.
[2]	肖克华, 罗稼昊, 饶宇. 航空发动机涡轮叶片尾缘楔形通道交错肋冷却实验[J]. 上海交通大学学报, 2022, 56(8): 1034-1042.
[3]	赵忠良, 李浩, 赖江, 杨海泳, 王晓冰, 李玉平. 导弹模型直气复合气动特性研究[J]. 空天防御, 2022, 5(3): 1-9.
[4]	吴王浩, 段旭, 张鑫, 陈丹, 徐振东. 高马赫数钝头体气动/传热一体化计算方法研究[J]. 空天防御, 2022, 5(3): 87-92.
[5]	程晨, 王晓亮. 考虑蒙皮透射率的飞艇热力学模型及其热特性[J]. 上海交通大学学报, 2021, 55(7): 868-877.
[6]	易仕和, 丁浩林. 适用高超声速飞行环境的超声速气膜冷却光学窗口研究进展[J]. 空天防御, 2021, 4(4): 1-13.
[7]	陈清华, 高伟, 苏国用, 关维娟, 秦汝祥, 季家东, 马杨斌. 基于激光点热源非稳态传热模型测固体材料热物性参数[J]. 上海交通大学学报, 2021, 55(4): 471-479.
[8]	田新亮. “软尾减阻”述评[J]. 上海交通大学学报, 2021, 55(2): 213-214.
[9]	王瑞, 肖瑶, 顾汉洋, 叶亚楠. 螺旋管内单相流动周向非均匀传热现象的数值模拟[J]. 上海交通大学学报, 2020, 54(7): 688-696.
[10]	王飞, 丁伟, 邓德衡, 吴小峰. 水下多缆多体拖曳系统运动建模与模拟计算[J]. 上海交通大学学报, 2020, 54(5): 441-450.
[11]	王锴，夏添，饶宇. 三通道旋流冷却流动与传热性能[J]. 上海交通大学学报, 2020, 54(5): 481-489.
[12]	赖生智，吴亚东，田杰，欧阳华. 不同叶顶间隙下压气机旋转不稳定性特性[J]. 上海交通大学学报, 2020, 54(3): 265-276.
[13]	郭军，陈作钢，戴原星，陈建平. 喷水推进器进流面获取方法及其应用[J]. 上海交通大学学报, 2020, 54(1): 1-9.
[14]	李煜, 程广益, 李宗阳, 窦怡彬, 蒋君庭. 固体火箭发动机喷管两相流动下的热固耦合研究[J]. 空天防御, 2020, 3(1): 1-9.
[15]	郭春雨1,刘恬1，赵庆新1，郝浩浩2. 短波中标称伴流场特性分析[J]. 上海交通大学学报（自然版）, 2019, 53(2): 170-178.