支板火箭引射冲压发动机引射模态燃烧流动 (Ⅰ)瞬时掺混燃烧流场的数值模拟

推进技术 ›› 2003, Vol. 24 ›› Issue (2): 160-165.

支板火箭引射冲压发动机引射模态燃烧流动 (Ⅰ)瞬时掺混燃烧流场的数值模拟

黄生洪,何国强,何洪庆

西北工业大学航天工程学院陕西西安 710072;西北工业大学航天工程学院陕西西安 710072;西北工业大学航天工程学院陕西西安 710072

发布日期:2021-08-15
基金资助:
国防科技重点实验室基金(00JS60.3.3ZK0401)

Combustion flow in ejecting mode of strutjet engine (Ⅰ) Flow simulation in simultaneous mixing and combustion

Coll. of Astronautics, Northwestern Polytechnical Univ. , Xi’ an 710072, China;Coll. of Astronautics, Northwestern Polytechnical Univ. , Xi’ an 710072, China;Coll. of Astronautics, Northwestern Polytechnical Univ. , Xi’ an 710072, China

Published:2021-08-15

摘要/Abstract

摘要： 针对一种适用于多种工作模态的支板火箭引射冲压组合发动机构型,Ma在0～1来流范围的瞬时掺混(SMC)引射燃烧流场进行了数值模拟。详细分析了低速模态SMC湍流流场的流动结构及特征,并对其Ma在0～1范围的性能进行了分析,结果Ma在大于等于0.7范围内获得了推力增强。结论认为该种构型的组合发动机适用于作为机载导弹的动力装置,而更低马赫数范围(包括Ma=0)内的推力增强取决于多种因素的优化匹配。

关键词: 火箭基组合动力循环;冲压火箭发动机;引射式冲压发动机;燃烧;数值仿真

Abstract: A configuration of strutjet engine in ejecting mode was investigated with numerical simulation. The flow structure and features of ejecting mode in static sea-level and zero to 1 Mach conditions were analyzed in detail. The performance results show that the strutjet engine gets thrust enhancement with Mach number greater or equal to 0.7. It is concluded that the StarJet engine of this configuration can be used as the propeller of air-launched missile and the thrust enhancement in lower range of Mach number including zero Mach needs to be optimized with multiple elements.

Key words: Rocket based combined cycle;Ducted rocket engine;Ejector ramjet engine;Combustion;Numerical simulation

黄生洪,何国强,何洪庆. 支板火箭引射冲压发动机引射模态燃烧流动 (Ⅰ)瞬时掺混燃烧流场的数值模拟[J]. 推进技术, 2003, 24(2): 160-165.