Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle

被引：16
|
作者：
Yao, Songbai [1 ,2 ]
Tang, Xinmeng [1 ,2 ]
Wang, Jianping [1 ,2 ]
机构：
[1] Peking Univ, CAPT, Ctr Combust & Prop, Coll Engn, Beijing, Peoples R China
[2] Peking Univ, Coll Engn, SKLTCS, Dept Mech & Engn Sci, Beijing, Peoples R China
来源：
INTERNATIONAL JOURNAL OF TURBO & JET-ENGINES | 2017年 / 34卷 / 01期
基金：
中国国家自然科学基金;
关键词：
rotating detonation; hollow combustor; Laval nozzle; simulations; HYDROGEN-OXYGEN MIXTURE; MECHANISM; WAVE;
D O I：
10.1515/tjj-2015-0052
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
The aim of the present paper is to investigate the propulsive performance of the hollow rotating detonation engine (RDE) with a Laval nozzle. Three-dimensional simulations are carried out with a one-step Arrhenius chemistry model. The Laval nozzle is found to improve the propulsive performance of hollow RDE in all respects. The thrust and fuel-based specific impulse are increased up to 12.60 kN and 7484.40 s, respectively, from 6.46 kN and 6720.48 s. Meanwhile, the total mass flow rate increases from 3.63 kg/s to 6.68 kg/s. Overall, the Laval nozzle significantly improves the propulsive performance of the hollow RDE and makes it a promising model among detonation engines.
引用
收藏
页码：49 / 54
页数：6
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