Film Cooling in a High-Pressure Subscale Combustion Chamber

被引：29

作者：

Arnold, R. ^{[1
]}

Suslov, D. I. ^{[1
]}

Haidn, O. J. ^{[1
]}

机构：

[1] DLR, German Aerosp Ctr, D-74239 Hardthausen, Germany

来源：

JOURNAL OF PROPULSION AND POWER | 2010年 / 26卷 / 03期

关键词：

PROPELLANT ROCKET ENGINES; HELIUM INJECTION; ROW; DOWNSTREAM; HISTORY; HOLES; SLOT; AIR;

D O I：

10.2514/1.47148

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

By the application of film cooling in addition to regenerative cooling, a considerable reduction in thermal and structural loads of rocket combustion-chamber walls can be reached. This paper discusses important influence parameters on film cooling in terms of efficiency of the injected film and wall temperature reduction. For the experimental investigations a high-pressure subscale combustion chamber operated with the cryogenic propellant combination LOX/GH(2) was used. A gaseous film with ambient tempered hydrogen was injected in the axial direction at the face plate. Typical film-cooling parameters such as film blowing rate, velocity ratio between film injection velocity and hot-gas velocity, circumferential slot positioning, and film injection slot height were investigated systematically at the European Research and Technology Test Facility P8.

引用

页码：428 / 438

页数：11

共 39 条

[1] Circumferential Film Cooling Effectiveness in a LOX/H2 Subscale Combustion Chamber [J].