Experimental study of discharge coefficient and cooling effectiveness for impingement effusion cooling in curved section

LUO Guo-liang; YANG Wei-hua; CAO Jun; SHI Rui; SONG Shuang-wen

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Experimental study of discharge coefficient and cooling effectiveness for impingement effusion cooling in curved section

更新时间：2026-07-07

- Experimental study of discharge coefficient and cooling effectiveness for impingement effusion cooling in curved section
- Vol. 26, Issue 8, (2011)
- 作者机构：
  
  1. 中国航空工业集团公司中国航空动力机械研究所,湖南,株洲,41200
  2. 南京航空航天大学能源与动力学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2011
- 稿件说明：
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LUO Guo-liang, YANG Wei-hua, CAO Jun, et al. Experimental study of discharge coefficient and cooling effectiveness for impingement effusion cooling in curved section[J]. 2011, 26(8).
DOI：

LUO Guo-liang, YANG Wei-hua, CAO Jun, et al. Experimental study of discharge coefficient and cooling effectiveness for impingement effusion cooling in curved section[J]. 2011, 26(8). DOI：

摘要

为了研究回流燃烧室弯曲段采用冲击发散冷却结构时的流量系数和冷却效率

设计了多种不同几何尺寸的实验件模型

分别对其流量系数和冷却效率进行了实验研究

得出如下结论:①弯曲段冲击发散冷却结构的流量系数较小

一般不会超过0.7.发散孔倾角为40°的流量系数要小于倾角为20°和30°的流量系数

流量系数随着发散孔纵向间距比的增大而减小.②弯曲段冲击发散冷却结构的冷却效率均随着吹风比的增大而增大

其冷却效率要明显高于直板冲击发散冷却结构

且这种差异随着吹风比的增大而逐渐减弱.

Abstract

In order to experimentally study the discharge coefficient and cooling effectiveness of impingement effusion cooling in curved section of combustion chamber

several test pieces with different geometrical dimensions were designed.The research results from experimental study show that: (1) The discharge coefficient of impingement effusion dimension in curved section is less than 0.7.The discharge coefficient of effusion hole angle 40° is larger than the discharge coefficient of effusion hole angle 30° and 20°

and the spacing between effusion holes has a great influence on the discharge coefficient. (2) The cooling effectiveness of impingement effusion in curved section is increased with the increase of blowing ration.And there is a large difference for the cooling effectiveness of impingement effusion between curved and flat sections

and the difference is decreased with the increase of blowing ratio.

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Related Author

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LU Cong-ming

Hong WEI

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Buming WAN

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Related Institution

China Aviation Powerplant Research Institute, Aviation Industry Corporation of China

School of Power and Energy,Northwestern Polytechnical University

Department of Aeronautics and Astronautics，Fudan University

School of Mechanical Engineering，Shanghai Jiao Tong University

Hunan Aviation Powerplant Research Institute， Aero Engine Corporation of China

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