超燃冲压发动机流量匹配机理

黄 兴; 陈玉春; 王晓东; 李 洁; 蔡元虎

doi:10.13224/j.cnki.jasp.2014.04.015

超燃冲压发动机流量匹配机理

doi: 10.13224/j.cnki.jasp.2014.04.015

西北工业大学动力与能源学院,西安 710072

详细信息

作者简介:
黄兴：黄兴(1983-),男,湖北荆州人,博士生,研究方向为发动机总体设计.

中图分类号: V235.113
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出版历程
- 收稿日期: 2013-01-30
- 刊出日期: 2014-04-28

Mechanism of mass flow matching in scramjet

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

摘要

摘要: 采用基于集总参数方程的燃烧室性能计算模型,辅以临界面积法,应用于隔离段和燃烧室的一维流场计算,实现了双模态超燃冲压发动机各种模态下的隔离段和燃烧室的流量匹配计算,并分析了流量匹配工作机理.结果表明:在未分离超燃模态与分离超燃模态下,增加燃烧室供油流量,隔离段和燃烧室流量匹配是通过流道中的喉道处马赫数降低来实现的;在跨燃模态与亚燃模态下,增加燃烧室供油流量,流量匹配主要是通过提高燃烧室流道中热力喉道处的总压来实现的.
- 双模态超燃冲压发动机 /
- 集总参数方程 /
- 临界面积法 /
- 流量匹配 /
- 总压
Abstract: Combustor performance computing model based on lumped parameter equations was used to simulate the 1-D flow field in the isolator and combustor along with the critical area method. The simulation of mass flow matching between isolator and combustor at every mode in dual-mode scramjet was achieved, and the mechanism of mass flow matching was analyzed. The results show that at the non-separation supersonic mode and the separation supersonic mode, the mass flow matching between isolator and combustor is achieved by lowering the Mach number at the throat when the fuel mass flow increases in combustor, while at the transonic mode and the subsonic mode, it is achieved by increasing the total pressure at the throat when the fuel mass flow increases in combustor.
- dual-mode scramjet /
- lumped parameter equations /
- critical area method /
- mass flow matching /
- total pressure

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参考文献(16)

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