Experimental Investigation on Performance of Pulse Detonation Rocket Engine Model

作     者：LI Qiang FAN Wei YAN Chuan-jun HU Cheng-qi YE Bin 

作者机构：School of Engine and Energy Northwestern Polytechnical University Xi＇an 710072 China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2007年第20卷第1期

页      面：9-14页

核心收录：

学科分类：080703[工学-动力机械及工程] 082502[工学-航空宇航推进理论与工程] 08[工学] 0807[工学-动力工程及工程热物理] 0825[工学-航空宇航科学与技术] 

基　　金：National Natural Science Foundation of China (501- 06012, 50336030) Program for New Century Excellent Talents in Uni-versity(NCET-04-0960) 

主　　题：pulse detonation rocket engine impulse nozzle experimental investigation 

摘      要：The PDRE test model used in these experiments utilized kerosene as the fuel, oxygen as oxidizer, and nitrogen as purge gas. The solenoid valves were employed to control intermittent supplies of kerosene, oxygen and purge gas. PDRE test model was 50 mm in inner diameter by 1.2 m long. The DDT （deflagration to detonation transition） enhancement device Shchelkin spiral was used in the test model. The effects of detonation frequency on its time-averaged thrust and specific impulse were experimentally investigated. The obtained results showes that the time-averaged thrust of PDRE test model was approximately proportional to the detonation frequency. For the detonation frequency 20 Hz, the time-averaged thrust was around 107 N, and the specific impulse was around 125 s. The nozzle experiments were conducted using PDRE test model with three traditional nozzles. The experimental results obtained demonstrated that all of those nozzles could augment the thrust and specific impulse. Among those three nozzles, the convergent nozzle had the largest increased augmentation, which was approximately 18%, under the specific condition of the experiment.