Airbreathing rotating detonation wave engine cycle analysis

被引：153

作者：

Braun, Eric M. ^{[1
]}

Lu, Frank K. ^{[1
]}

Wilson, Donald R. ^{[1
]}

Camberos, Jose A. ^{[2
]}

机构：

[1] Univ Texas Arlington, Arlington, TX 76019 USA

[2] USAF, Res Lab, Wright Patterson AFB, OH 45433 USA

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2013年 / 27卷 / 01期

关键词：

Detonation; Cycle analysis; Propulsion system; PROPAGATION; PERFORMANCE; PROPULSION; AIR;

D O I：

10.1016/j.ast.2012.08.010

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

A cycle analysis model for an airbreathing, rotating detonation wave engine (RDE) is presented. The engine consists of a steady inlet system with an isolator which delivers air into an annular combustor. A detonation wave continuously rotates around the combustor with side relief as the flow expands towards the nozzle. A model for the side relief is used to find the pressure distribution around the combustor. Air and fuel enter the combustor when the rarefaction wave pressure behind the detonation front drops to the inlet supply pressure. To create a stable RDE, the inlet pressure is matched in a convergence process with the average combustor pressure by increasing the annulus channel radial width with respect to the isolator channel. Performance of this engine is considered using several parametric studies and compared with rocket-mode computational results. A hydrogen-air RDE reaches a specific impulse of 3800 s and can reach a flight speed of Mach 5. (C) 2012 Elsevier Masson SAS. All rights reserved.

引用

页码：201 / 208

页数：8

共 41 条

[1]

Anderson J.D., 2002, MODERN COMPRESSIBLE, V3rd

[2]

[Anonymous], PROGR ASTRONAUTICS A

[3]

[Anonymous], 2001211080 NASA TM

[4]

[Anonymous], THESIS U POITIERS

[5]

[Anonymous], FM2006006 GALCIT CAL

[6]

[Anonymous], 1964, RPLTDR64113 MICH U

[7]

[Anonymous], 1994, AIAA ED SERIES

[8]

[Anonymous], 121194 NASA CR

[9]

[Anonymous], 33 AIAA ASME SAE ASE

[10]

[Anonymous], 1999, THESIS CALTECH

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