脉冲爆震涡轮发动机研究进展  

Research progress on pulse detonation turbine engine

作　　者：郑龙席[1] 卢杰[1] 严传俊[1] 邱华[1] 王治武[1] 黄希桥[1] 李晓丰[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2014年第5期993-1000,共8页Journal of Aerospace Power

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.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.

关 键 词：脉冲爆震波 脉冲爆震燃烧室 涡轮 涡轮发动机 脉冲爆震涡轮发动机 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]