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脉冲爆震涡轮发动机研究进展

郑龙席,  卢杰,  严传俊,  邱华,  王治武,  黄希桥,  李晓丰

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文章导航 > 航空动力学报  > 2014 >  (5): 993-1000
郑龙席, 卢杰, 严传俊, 邱华, 王治武, 黄希桥, 李晓丰. 脉冲爆震涡轮发动机研究进展[J]. 航空动力学报, 2014, (5): 993-1000.
引用本文: 郑龙席, 卢杰, 严传俊, 邱华, 王治武, 黄希桥, 李晓丰. 脉冲爆震涡轮发动机研究进展[J]. 航空动力学报, 2014, (5): 993-1000.
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ZHENG Long-xi, LU Jie, YAN Chuan-jun, QIU Hua, WANG Zhi-wu, HUANG Xi-qiao, LI Xiao-feng. Research progress on pulse detonation turbine engine[J]. Journal of Aerospace Power, 2014, (5): 993-1000.
Citation: ZHENG Long-xi, LU Jie, YAN Chuan-jun, QIU Hua, WANG Zhi-wu, HUANG Xi-qiao, LI Xiao-feng. Research progress on pulse detonation turbine engine[J]. Journal of Aerospace Power, 2014, (5): 993-1000.
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脉冲爆震涡轮发动机研究进展

  • 西北工业大学 动力与能源学院, 西安 710072

详细信息
    作者简介:

    郑龙席（1970- ），男，陕西西安人，教授、博士生导师，博士，研究领域为航空发动机燃烧与流动，新概念航空航天推进技术，航空发动机强度、振动与可靠性.

  • 中图分类号: V235

Research progress on pulse detonation turbine engine

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

    摘要
  • 摘要: 介绍了脉冲爆震涡轮发动机的基本概念、主要结构形式以及基本特点.详细介绍了国内外研究状况及课题组的最新研究进展，对脉冲爆震涡轮发动机需要突破的关键技术、主要研究内容以及发展途径进行了探讨.研究表明：相比于传统的涡轮喷气发动机，脉冲爆震涡轮发动机的耗油率能降低5%~15%；在相同的燃烧室入口条件下，与等压燃烧驱动涡轮相比，用脉冲爆震燃烧驱动涡轮时的涡轮的单位输出功率要高；实现了由脉冲爆震燃烧室驱动涡轮，涡轮带动压气机给脉冲爆震燃烧室供气的自吸气模式，表明用脉冲爆震燃烧室代替传统等压燃烧室是完全可行的.

     

    Abstract: Basic concept,main structures and primary characteristics were reviewed of pulse detonation turbine engine.A detail trend at home and abroad of its development was presented;the results of our recent experimental researches were summarized;the key technology and research areas of pulse detonation turbine engine were discussed.Performance calculations show that the specific fuel consumption of pulse detonation turbine engine could have a reduction about 5% to 15% compared with that of traditional turbine jet engine. The specific power of the turbine driven by pulse detonation combustor is higher than that driven by constant pressure combustor under the same inlet conditions of the combustors.A self-aspirated model was successfully achieved by driving the turbine with pulse detonation combustor whose oxidant was supplied by the turbine driven compressor.The results verify the feasibility of substituting the traditional constant pressure combustor with pulse detonation combustor.

     

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  • 收稿日期:  2013-03-19
  • 刊出日期:  2014-05-28

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