| 煤油/空气三管脉冲爆震发动机共用尾喷管研究 |
| |
| 引用本文： | 李建中,王家骅,唐豪,潘波.煤油/空气三管脉冲爆震发动机共用尾喷管研究[J].航空动力学报,2008,23(5):840-844. |
| |
| 作者姓名： | 李建中 王家骅 唐豪 潘波 |
| |
| 作者单位： | 1. 南京航空航天大学,能源与动力学院,南京,210016
2. 总参谋部陆航研究所,直升机与发动机研究室,北京,101114 |
| |
| 基金项目： | 国家自然科学基金
,
南京航空航天大学校科研和教改项目 |
| |
| 摘 要： | 探索脉冲爆震-涡扇组合发动机的可行性,建立了煤油/空气三管气动阀式脉冲爆震发动机PDE试验系统,设计、加工了收敛型尾喷管和收敛-扩张型尾喷管,在三个内径100 mm,长2 000 mm的爆震管内获得了充分发展的爆震波,成功实现总工作频率30 Hz稳定时序工作,研究了三管PDE各爆震管之间爆震燃烧特性的相互影响规律.三管PDE安装共用尾喷管能够提高爆震室内压力,提高三管PDE的工作性能.研究结果为研制多管脉冲爆震发动机原理样机提供了理论依据.
|
| 关 键 词： | 航空、航天推进系统 脉冲爆震-涡扇组合发动机(PDTE) 脉冲爆震发动机(PDE) 爆震燃烧 多管 气动阀 |
| 文章编号： | 1000-8055(2008)05-0840-05 |
| 收稿时间： | 2007/5/17 0:00:00 |
| 修稿时间： | 2007年5月17日 |
Investigation on common nozzle of triple-tube pulse detonation engine with kerosene/air |
| |
| LI Jian-zhong,WANG Jia-hu,TANG HaoPAN Bo.Investigation on common nozzle of triple-tube pulse detonation engine with kerosene/air[J].Journal of Aerospace Power,2008,23(5):840-844. |
| |
| Authors: | LI Jian-zhong WANG Jia-hu TANG HaoPAN Bo |
| |
| Affiliation: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;PAL Headquarter of the General Staff Army Research Institute, Beijing 101114, China |
| |
| Abstract: | To explore the feasibility of pulse detonation-turbofan combined engine(PDTE), a whole test system of kerosene/air triple-tube aero-valve pulse detonation engine(PDE) was established.A converging nozzle and a converging-diverging nozzle were designed.Within detonation tube of 100 mm in inner diameter and 2 000 mm in length,triple-tube PDE could be operated at 30 Hz in total frequency,and the fully-developed detonation waves were successfully achieved.The effect of interaction among detonation tubes on detonation combustion properties of triple-tube pulse detonation engine was investigated.Because the detonation pressure in tube of triple-tube PDE with common nozzle was raised,the performance of triple-tube pulse detonation engine was improved.The results lay a basis for preliminary design of practical multi-tube pulse detonation engine. |
| |
| Keywords: | aerospace propulsion system pulse detonation-turbofan combined engine(PDTE) pulse detonation engine(PDE) detonative combustion multi-tube aero-valve |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
|
点击此处可从《航空动力学报》下载全文 |
|
