脉冲爆震发动机尾喷管的实验

范玮; 严传俊; 李强; 胡承启; 叶斌

脉冲爆震发动机尾喷管的实验

西北工业大学动力与能源学院, 西安 710072

基金项目: 国家自然科学基金资助(5010601250336030);教育部新世纪优秀人才计划资助(NCET-04-0960)

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出版历程
- 收稿日期: 2006-06-05
- 修回日期: 2006-10-10
- 刊出日期: 2007-06-28

Experimental investigation on pulse detonation engine nozzles

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

摘要

摘要: 选取3类10种有代表性的脉冲爆震发动机尾喷管进行了试验.研究结果表明, 各种喷管对性能均有提高;对每类喷管均存在一最佳面积比, 使推力增益最大;在受试的尾喷管中, 收敛-扩张喷管增益最大, 达24%;填充系数对喷管性能增益影响甚微.
- 航空、航天推进系统 /
- 脉冲爆震发动机 /
- 尾喷管 /
- 推力增益 /
- 实验研究
Abstract: 10 nozzles from 3 typical types are chosen under experimental tests.The results show that all nozzles can augment the thrust of baseline pulse detonation engine(PDE)and there is an optimal nozzle area ratio where thrust augmentation is maximized.Amongst all tested nozzles,the maximal augmentation of 24% is attained by a convergent-divergent nozzle.Moreover,it is validated that fill-fraction has little effect on thrust augmentation.
- aerospace propulsion system /
- pulse detonation engine(PDE) /
- nozzle /
- thrust augmentation /
- experimental study

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参考文献(10)

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