MMH/NTO火箭发动机燃烧动态稳定性数值评定

推进技术 ›› 2001, Vol. 22 ›› Issue (2): 155-156.

MMH/NTO火箭发动机燃烧动态稳定性数值评定

庄逢辰,张中光,聂万胜,邹勤

装备指挥技术学院!北京101400;上海动力机械研究所!上海200233;装备指挥技术学院!北京101400;装备指挥技术学院!北京101400

发布日期:2021-08-15
基金资助:
国家“八六三”基金资助项目

Numerical assessment of MMH/NTO rocket engine combustion instability

Inst. of Equipment Command and Technology, Beijing 101400,China;Shanghai Inst.of Power Machinery, Shanghai 200233,China;Inst. of Equipment Command and Technology, Beijing 101400,China;Inst. of Equipment Command and Technology, Beijing 101400,China

Published:2021-08-15

摘要/Abstract

摘要： 应用脉冲枪不稳定燃烧模型对有 /无声腔的MMH/NTO火箭发动机的燃烧稳定性进行了数值模拟 ,比较了 3台MMH/NTO发动机的燃烧动态稳定性 ,计算与发动机的试车结果一致。

关键词: 流动推进剂火箭发动机;燃烧稳定性;脉冲枪模型;数值仿真;数值分析

Abstract: A given MMH/NTO rocket engine combustion stability with/without acoustic cavities was numerically simulated by pulse gun combustion instability model.Three MMH/NTO rocket engines combustion dynamic stabilities were compared and assessed. Numerical simulation and assessment results are agreeable with the engine hot test data.

Key words: Liquid propellant rocket engine;Combustion stability;Pulse gun model;Numerical simulation;Numerical analycis

庄逢辰,张中光,聂万胜,邹勤. MMH/NTO火箭发动机燃烧动态稳定性数值评定[J]. 推进技术, 2001, 22(2): 155-156.