Injector-Driven Flame Dynamics in a High-Pressure Multi-Element Oxygen-Hydrogen Rocket Thrust Chamber

被引：36

作者：

Armbruster, Wolfgang ^{[1
]}

Hardi, Justin S. ^{[2
]}

Suslov, Dmitry ^{[3
]}

Oschwald, Michael ^{[4
]}

机构：

[1] DLR, Inst Space Prop, D-74239 Hardthausen, Germany

[2] DLR, Inst Space Prop, Combust Dynam, D-74239 Hardthausen, Germany

[3] DLR, Inst Space Prop, Combust Chamber Technol, D-74239 Hardthausen, Germany

[4] DLR, Inst Space Prop, Rocket Prop Dept, D-74239 Hardthausen, Germany

来源：

JOURNAL OF PROPULSION AND POWER | 2019年 / 35卷 / 03期

关键词：

EXCITED COMBUSTION INSTABILITIES; DECOMPOSITION; ORIFICE;

D O I：

10.2514/1.B37406

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

This work addresses the nature of supercritical hydrogen-oxygen flame coupling to acoustics through visualization under conditions representative of upper-stage rocket engines. A research thrust chamber that shows self-excited combustion instabilities for certain operating conditions was used. Previous analysis proved that the instabilities are connected to injector acoustics. In this study a small optical access window was mounted in the chamber wall. Highspeed flame radiation imaging of UV and blue wavelengths has been applied in order to analyze the acoustic-flame interaction of one of the 42 flames. Dynamic mode decomposition results for a case with 80-bar chamber pressure showed that the flame dynamics are strongly influenced by theLOXinjector acoustics, whereas for a 50-bar chamber pressure load point no flame response to injector acoustics was observed. A potential source of acoustic excitation in the oxygen injectors based on hydrodynamic effects is consistent with the observations from the two load points.

引用

页码：632 / 644

页数：13