带造型凹坑孔的平板气膜冷却特性研究

张子寒; 何坤; 晏鑫

doi:10.7652/xjtuxb202007011

您当前的位置：

首页 >

文章列表页 >

带造型凹坑孔的平板气膜冷却特性研究

更新时间：2025-07-09

- 带造型凹坑孔的平板气膜冷却特性研究
- Investigation on the Film Cooling Efficiency on a Plain Surface with Hole Embedded in Contoured Crater
- 西安交通大学学报 2020年54卷第7期页码：84-93
- 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：
  
  : 2020-01-07。作者简介: 张子寒(1995—),男,博士生;何坤(通信作者),女,副教授。基金项目: 国家自然科学基金资助项目(51306138);陕西省自然科学基金资助项目(2018JQ5109)
- DOI：10.7652/xjtuxb202007011
  中图分类号： TK474.7
- 网络首发：2020-07-10，
  
  纸质出版：2020
- 稿件说明：
移动端阅览
张子寒, 何坤, 晏鑫. 带造型凹坑孔的平板气膜冷却特性研究[J]. 西安交通大学学报, 2020,54(7):84-93.

Investigation on the Film Cooling Efficiency on a Plain Surface with Hole Embedded in Contoured Crater[J]. 2020, 54(7): 84-93.
张子寒, 何坤, 晏鑫. 带造型凹坑孔的平板气膜冷却特性研究[J]. 西安交通大学学报, 2020,54(7):84-93. DOI： 10.7652/xjtuxb202007011.

Investigation on the Film Cooling Efficiency on a Plain Surface with Hole Embedded in Contoured Crater[J]. 2020, 54(7): 84-93. DOI： 10.7652/xjtuxb202007011.

摘要

设计了一种造型凹坑冷却孔结构

采用数值求解雷诺平均Navier-Stokes方程的方法

研究了造型凹坑孔结构对平板气膜冷却性能的影响

并利用已有的实验数据考核了数值方法的有效性。通过计算得到了6种吹风比、3种凹坑深度条件下带造型凹坑孔的平板气膜冷却性能

并与常规圆孔进行了对比。研究结果表明:在考核的7种湍流模型中

Realizable k-ε湍流模型可以较好地模拟平板壁面的冷却性能; 造型凹坑孔可以产生一对阻碍肾形涡发展的反向旋涡

降低冷却流体与高温主流的掺混作用

增加冷却流体在周向上的覆盖

从而提高气膜冷却效率; 相比于常规圆孔结构

造型凹坑孔可以有效地提高轴向中心线及周向平均气膜冷却效率

在不同吹风比条件下

造型凹坑孔的气膜冷却效率在轴向长度为3倍孔径的区域提高了20%～200%

在3倍到10倍孔径的区域提高了10%～25%; 在所研究的3种凹坑深度中

凹坑深度为圆孔直径的0.7倍时平板气膜冷却性能最优。

Abstract

A contoured crater cooling hole was designed. With solutions of RANS(Reynolds-averaged Navier-Stokes)equations

the film cooling efficiency on a plain surface with cooling hole embedded in contoured crater was investigated. With the existing experimental data

the reliability of numerical methods was validated. Then

the influences of blowing ratio and crater depth on the cooling efficiency were studied. The numerical results for plain surface with cooling hole embedded in contoured crater were also compared with that of the conventional round hole configuration. The results show that

among all selected turbulence models

the Reali-able k-- turbulence model has the superior accuracy in predicting the cooling efficiency on plain surface. The cooling hole embedded in contoured crater is able to generate a pair of reverse vortices that hinder the development of kidney vortices

reducing the mixing effect of coolant and high temperature mainstream. Correspondingly

the coverage of coolin

关键词

Keywords

references

SMITH S H, MUNGAL M G. Mixing, structure and scaling of the jet in crossflow [J]. Journal of Fluid Mechanics, 1998, 357: 83-122.

GOLDSTEIN R J, ECKERT E R G, BURGGRAF F. Effects of hole geometry and density on three-dimensional film cooling [J]. International Journal of Heat and Mass Transfer, 1974, 17(5): 595-607.

HAVEN B A, YAMAGATA D K, KUROSAKA M, et al. Anti-kidney pair of vortices in shaped holes and their influence on film cooling effectiveness [C/OL]∥ ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. [2019-12-20].10. 1115/97-GT-045.

朱惠人, 许都纯, 刘松龄, 等. 簸箕形排孔气膜冷却实验研究 [J]. 航空学报, 1997, 18(5): 25-28.

ZHU Huiren, XU Duchun, LIU Songling, et al. Film cooling experimental investigation of a row of dust pan shaped holes [J]. Acta Aeronautica et Astronautica Sinica, 1997, 18(5): 25-28.

刘存良, 朱惠人, 白江涛. 收缩-扩张形气膜孔提高气膜冷却效率的机理研究 [J]. 航空动力学报, 2008, 23(4): 598-604.

LIU Cunliang, ZHU Huiren, BAI Jiangtao. Study on the physics of film-cooling effectiveness enhancement by the converging-expanding hole [J]. Journal of Aerospace Power, 2008, 23(4): 598-604.

李广超, 柏树生, 吴冬, 等. 气膜孔形状对涡轮叶片气膜冷却影响的研究进展 [J]. 热能动力工程, 2010, 25(6): 581-585.

LI Guangchao, BAI Shusheng, WU Dong, et al. Recent advances in the study of influence of air-film hole shapes on turbine blade air-film cooling [J]. Journal of Engineering for Thermal Energy and Power, 2010, 25(6): 581-585.

刘晓红, 罗翔, 陶智. 小孔辅助射流提高气膜冷却效率的机理分析 [J]. 航空动力学报, 2010, 25(10): 2267-2272.

LIU Xiaohong, LUO Xiang, TAO Zhi. Analysis on improvement of film cooling effectiveness with small coolant jets [J]. Journal of Aerospace Power, 2010, 25(10): 2267-2272.

LU Y P. Effect of hole configurations on film cooling from cylindrical inclined holes for the application to gas turbine blades [D]. Baton Rouge, LA, USA: Louisiana State University, 2007.

HOLLOWAY D S, LEYLEK J H, BUCK F A. Pressure-side bleed film cooling: part I Steady framework for experimental and computational results [C]∥ ASME Turbo Expo 2002: Power for Land, Sea, and Air. New York, USA: ASME, 2009: 835-843.

SARKAR S, RANAKOTI G. Effect of vortex generators on film cooling effectiveness [J]. Journal of Turbomachinery, 2017, 139(6): 061009.

NASIR H, ACHARYA S, EKKAD S. Improved film cooling from cylindrical angled holes with triangular tabs: effect of tab orientations [J]. International Journal of Heat and Fluid Flow, 2003, 24(5): 657-668.

FRIC T F, CAMPBELL R P. Method for improving the cooling effectiveness of a gaseous coolant stream which flows through a substrate, and related articles of manufacture: US6383602 B1 [P]. 2002-05-07.

章大海, 王振波, 曲燕, 等. 开槽气膜孔结构对气膜冷却和流动特性的影响 [J]. 燃气轮机技术, 2010, 23(4): 27-32.

ZHANG Dahai, WANG Zhenbo, QU Yan, et al. The influence of trenched film hole configurations on film cooling and flowing characteristics [J]. Gas Turbine Technology, 2010, 23(4): 27-32.

戴萍, 林枫. 新型缩放槽缝孔气膜冷却效率的数值研究 [J]. 汽轮机技术, 2009, 51(1): 1-4.

DAI Ping, LIN Feng. Numerical study on film cooling effectiveness from converging slot-hole [J]. Turbine Technology, 2009, 51(1): 1-4.

KALGHATGI P, ACHARYA S. Improved film cooling effectiveness with a round film cooling hole embedded in a contoured crater [J]. Journal of Turbomachinery, 2015, 137(10): 101006.

SINHA A K, BOGARD D G, CRAWFORD M E. Film-cooling effectiveness downstream of a single row of holes with variable density ratio [J]. Journal of Turbomachinery, 1991, 113(3): 442-449.

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

张角凹坑气膜孔对双层壁气膜冷却特性的影响

面向气膜冷效提升的涡轮叶栅全端壁非轴对称造型设计优化

单介质阻挡放电等离子体激励对平板气膜冷却性能的影响

吹风比和湿空气含湿量对平板气膜冷却流动与传热特性的影响

气膜孔堵塞对凹槽叶顶冷却传热性能的影响