多循环脉冲爆震发动机推力测试试验

推进技术 ›› 2012, Vol. 33 ›› Issue (2): 317-321.

多循环脉冲爆震发动机推力测试试验

何小明,李建中,王家骅,张靖周

南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016

发布日期:2021-08-15
作者简介:何小明(1972—),男,博士,讲师,研究领域为工程热物理。E-mail:vehicle@nuaa.edu.cn

Experiments on Thrust Measurement of Multi-Cycle Pulse Detonation Engine

College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Published:2021-08-15

摘要/Abstract

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。

关键词: 脉冲爆震发动机;总压损失;推力直接测量

Abstract: 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 114mm 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. 

Key words: Pulse detonation engine; Overall pressure loss; Thrust measurement directly

何小明,李建中,王家骅,张靖周. 多循环脉冲爆震发动机推力测试试验[J]. 推进技术, 2012, 33(2): 317-321.

参考文献

[2] 刘大响,彭友梅.新概念航空发动机展望[J].现代军事, 3,2:12-15.
[3] Wintenberger E,Austin J M,Cooper M,et al．An Analytical Model for the Impulse of a Single-Cycle Pulse Detonation Engine[R]．AIAA 2001-3811．
[4] Cooper M,Jackson S,Austin J,et al．Direct Experimental Impulse Measurements for Detonations and Deflagrations[R]．AIAA 2001-3812．
[5] Zitoun R,Desbordes D．Propulsive Performances of Pulsed Detonations[J]．Combustion Science and Technology,9,4:93-114.
[6] Ishii K,Tanaka T,Ami K.Development of a New Detonator Using Multiple Tubes for Pulse Detonation Engines[R].AIAA 2002-5168.
[7] Tomoaki Yatsufusa, Masahiro Ohira, Shin’ichi Yamamoto.Development of Liquid-Fuel Initiator for Liquid-Fuel PDE[R].AIAA 2004-1213.
[8] Jiro Kasahara,Masao Hirano.Flight Experiments Regarding Ethylene-Oxygen Single-Tube Pulse Detonation Rockets[R].AIAA 2004-3918.
[9] Hidetoshi Shimada,Yasuhiro Kenmoku,Hiroyuki Sato,et al.A New Ignition System for Pulse Detonation Engine[R].AIAA 2004-308.
[10] Kasahara J,Tanahashi Y,Hirano M,et al.Experiment Investigation of Momentum and Heat Transfer in Pulse Detonation Rockets[R].AIAA 2004-869.
[11] 何立明,严传俊,范玮．脉冲爆震发动机的推力计算方法[J]．推进技术,1997,18(5)．(HE Li-ming,YAN Chuan-jun,FAN Wei.A Method of Calculating Thrust of Pulsed Detonation Engines[J].Journal of Propulsion Technology,7,8(5).)
[12] 李建中,王家骅,范育新,等.多循环脉冲爆震发动机净推力估算[J].推进技术 2004,25(3):241-245.(LI Jian-zhong,WANG Jia-Hua,FAN Yu-xin,et al.Net Thrust Prediction of Multi-Cycle Pulse Detonation Engine[J].Journal of Propulsion Technology,4,5(3).)
[13] 张义宁,王家骅,张靖周.多循环吸气式脉冲爆震发动机推力直接测量[J].推进技术 2006,27(5):459-462.(ZHANG Yi-ning,WANG Jia-hua,ZHANG Jing-zhou.Impulse of Cyclic Air-Breathing Pulse Detonation Engine[J].Journal of Propulsion Technology,6,7(5).)