Rotating detonation engines with two fuel orifice schemes

被引：20

作者：

Wang, Yuhui ^{[1
]}

Le, Jialing ^{[2
]}

机构：

[1] Beijing Univ Chem Technol, Coll Mech & Elect Engn, Beijing 100029, Peoples R China

[2] China Aerodynam Res & Dev Ctr, Mianyang 621000, Sichuan, Peoples R China

来源：

ACTA ASTRONAUTICA | 2019年 / 161卷

基金：

中国国家自然科学基金;

关键词：

Rotting detonation engine; Fuel orifice; Hydrogen; Surface roughness; High-speed imaging; HYDROGEN; ETHYLENE; COMBUSTION; WAVE;

D O I：

10.1016/j.actaastro.2019.05.035

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Hollow combustors without centerbodies are becoming popular for rotating detonation engines. The present experimental study compares detonation and pressure gain performances of hollow combustors with two fuel orifice schemes to choose a better one. Hydrogen and air sources at room temperatures of 280-285 K are used as propellants. The combustors are optically accessible by embedding a piece of quartz glass in the outerbody. The hollow combustor channel here has an outer diameter of 100 mm. Fuel is injected into the combustor from 150 cylindrical orifices in a diameter of 0.8 mm or 90 orifices in a diameter of 2 mm, and air is injected through a circular channel with a throat width of 1 mm. Results show that the hollow combustor with 150 cylindrical orifices in a diameter of 0.8 mm has a better detonation performance and a higher pressure gain performance than the other one. High-speed images show the wall surface roughness affects the RDW strength greatly.

引用

页码：262 / 275

页数：14

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