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

作者：Yao, Songbai^*; Tang, Xinmeng; Wang, Jianping

来源：INTERNATIONAL JOURNAL OF TURBO & JET-ENGINES, 2017, 34(1): 49-54.

DOI：10.1515/tjj-2015-0052

• rotating detonation
• hollow combustor
• Laval nozzle
• simulations

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.

• 出版日期2017-4
• 单位北京大学