多循环脉冲爆震发动机推力测试试验  

Experiments on Thrust Measurement of Multi-Cycle Pulse Detonation Engine

作　　者：何小明[1] 李建中[1] 王家骅[1] 张靖周[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2012年第2期317-321,共5页Journal of Propulsion Technology

摘　　要：为了准确、可靠地直接测量多循环脉冲爆震发动机的推力,建立冷态阻力和热态净推力直接测量系统,针对内径114mm、长1100mm的气动阀式脉冲爆震发动机,研究冷态吹风条件下发动机及其主要部件的总压恢复、阻力损失等特性,验证推力测量系统有效地将射流试验条件下外溢气流对脉冲爆震发动机外部及其附件造成的阻力转移到支撑台架上,消除外溢气流对发动机推力测量的影响。开展大量的爆震燃烧试验,实现了脉冲爆震发动机达到40Hz稳定工作,并获得充分发展的爆震波,利用高频响动态推力传感器测量获得脉冲爆震发动机动态净推力变化规律。In order to measure directly the thrust of multi-cycle pulse detonation engine, the rig of drag and net thrust measurement was established. With a detonation tube 114ram in inner diameter and 1100mm in length, the characteristics of overall pressure recovery and flow drag loss of pulse detonation engine and the main parts was investigated with filling air. The drag of overflow of pulse detonation engine and the accessory was devolved to the rig and the influence of overflow on thrust was eliminated. Much detonation experimentation was carried out and the kerosene/air aero-valve pulse detonation engine could be operated at 40Hz in frequency. The net thrust of pulse detonation engine was measured with high frequency dynamic thrust sensor and the variety course was obtained. This investigation is of importance to establish basics for investigating thoroughly the propulsion performance of pulse detonation engine.

关 键 词：脉冲爆震发动机 总压损失 推力直接测量 

分 类 号：V235.22[航空宇航科学与技术—航空宇航推进理论与工程]