脉冲爆震涡轮发动机增推装置性能试验

doi:10.7527/S1000-6893.2015.0083

流体力学与飞行力学

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脉冲爆震涡轮发动机增推装置性能试验

邱华, 徐泽阳, 郑龙席, 段小瑶

西北工业大学动力与能源学院, 西安 710072

收稿日期:2015-01-13 修回日期:2015-03-25 出版日期:2016-02-15 发布日期:2015-04-21
通讯作者: 邱华,男,博士,副教授。主要研究方向:爆震推进应用基础研究,发动机燃烧与流动,非定常推进中的能量高效提取与转化。Tel:029-88492414,E-mail:qiuhua@nwpu.edu.cn E-mail:qiuhua@nwpu.edu.cn
作者简介:徐泽阳,男,硕士研究生。主要研究方向:脉冲爆震涡轮发动机相关技术。E-mail:370881832@qq.com;郑龙席,男,博士,教授,博士生导师。主要研究方向:脉冲爆震发动机应用基础研究,航空发动机中的燃烧与流动,动力机械的结构、强度、振动、寿命及可靠性。Tel:029-88492414,E-mail:zhenglx@nwpu.edu.cn;段小瑶,男,硕士研究生。主要研究方向:脉冲爆震涡轮发动机相关技术。E-mail:550557422@qq.com
基金资助:
国家自然科学基金(50906072,51306154);中央高校基本科研业务费专项资金(3102014JCY01003);陕西省自然科学基础研究计划(2015JM5221)

Tests of pulse detonation turbine engine performance with thrust augmentation devices

QIU Hua, XU Zeyang, ZHENG Longxi, DUAN Xiaoyao

School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

Received:2015-01-13 Revised:2015-03-25 Online:2016-02-15 Published:2015-04-21
Supported by:
National Natural Science Foundation of China(50906072,51306154);the Fundamental Research Funds for the Central Universities(3102014JCY01003);Natural Science Basic Research Plan in Shaanxi Province of China(2015JM5221)

摘要/Abstract

摘要：

以液态汽油为燃料,通过在双管脉冲爆震涡轮发动机(PDTE)原理样机的涡轮出口加装不同喷管和引射器等增推装置,利用试验研究了不同增推装置对自吸气工作模式下(工作频率10~20 Hz)发动机工作状态及推进性能的影响。结果表明:虽然加装3种尾喷管之后涡轮转速、压气机增压比及压气机流量都有不同程度的下降,但发动机都获得了不同程度的推力增益;相比于工作频率20 Hz时无喷管发动机推力114.95 N,发动机加装尾喷管后最大推力可达143.3 N,实现增推24.7%,最大单位推力为749.87 N·s/kg;加装引射器后可以进一步增推,发动机最大推力达到200.67 N,实现增推39.8%,同时这种增推效果随着工作频率的升高而逐渐增大。

关键词: 脉冲爆震涡轮发动机, 喷管, 引射器, 推进性能, 自吸气

Abstract:

To acquire experimental propulsive performance of pulse detonation turbine engine(PDTE), thrust augmentation devices, such as converge/diverge nozzles and ejector, are installed on the turbine exit of two-tube PDTE experimental system. Experimental investigations are carried out to research the influences of thrust augmentation devices on the working condition and propulsive performance of PDTE. The PDTE experimental system is in the self-airbreathing working mode with working frequency from 10 Hz to 20 Hz. Liquid gasoline is used as fuel. Results show that the turbine speed, compression ratio and flow of compressor are all decreased with different degrees when converge/diverge nozzles are installed to the PDTE experimental system. However, the engine thrust is increased with the use of nozzles. Compared with the system without nozzle(thrust of which is 114.95 N at working frequency 20 Hz), the maximum thrust of the system with nozzle is 143.3 N and the thrust augmentation is 24.7%. And the maximum specific thrust is 749.87 N·s/kg. The thrust of the PDTE experimental system can be further increased with the installation of ejector to the system with nozzle. The maximum thrust at this condition is 200.67 N and the thrust augmentation is 39.8%. And the thrust augmentation can still be increased with the increase of working frequency.

Key words: pulse detonation turbine engine, nozzle, ejector, propulsive performance, air breathing

中图分类号:

V231.2

邱华, 徐泽阳, 郑龙席, 段小瑶. 脉冲爆震涡轮发动机增推装置性能试验[J]. 航空学报, 2016, 37(2): 522-532.

QIU Hua, XU Zeyang, ZHENG Longxi, DUAN Xiaoyao. Tests of pulse detonation turbine engine performance with thrust augmentation devices[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(2): 522-532.

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E-mail：hkxb@buaa.edu.cn

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脉冲爆震涡轮发动机增推装置性能试验

Tests of pulse detonation turbine engine performance with thrust augmentation devices

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