液体火箭发动机燃烧室声腔建模方法研究

推进技术 ›› 1999, Vol. 20 ›› Issue (6): 19-22.

液体火箭发动机燃烧室声腔建模方法研究

洪鑫,程惠尔,陈杰

上海交通大学工程热物理与能源研究所!上海;200030;上海交通大学工程热物理与能源研究所!上海;200030;上海交通大学工程热物理与能源研究所!上海;200030

发布日期:2021-08-15

MODELING METHODS OF ACOUSTIC CAVITY IN COMBUSTION CHAMBER OF LIQUID ROCKET ENGINE

Inst.of Thermophysics & Energy,Shanghai Jiao Tong Univ.,Shanghai,200030;Inst.of Thermophysics & Energy,Shanghai Jiao Tong Univ.,Shanghai,200030;Inst.of Thermophysics & Energy,Shanghai Jiao Tong Univ.,Shanghai,200030

Published:2021-08-15

摘要/Abstract

摘要： 基于数值模拟技术及有关振动理论，提出了一种建立液体火箭发动机燃烧室声腔模型的方法。为验证方法的可行性，建立了用于带声腔燃烧室全场数值模拟的分区解法，利用这两种方法对同一过程进行的计算表明建模方法是可行的

关键词: 液体推进剂火箭发动机;燃烧室;声学性质;燃烧稳定性;数值仿真;分区解法~+

Abstract: Based on the numerical simulation technology and fundamental vibration theory, a preliminary study was carried out for the method of modeling the effect of acoustic cavity on combustion instability in the combustion chamber of liquid rocket engine. In order to validate the method, it also developed a zonal method for numerical simulation of combustion chamber with acoustic cavity. The computation results demonstrate that the modeling method of acoustic cavity proposed is feasible.

Key words: Liquid propellant rocket engine;Combustion chamber;Acoustic property;Combustion stability;Numerical simulation;Zonal method +

洪鑫,程惠尔,陈杰. 液体火箭发动机燃烧室声腔建模方法研究[J]. 推进技术, 1999, 20(6): 19-22.