液氧/烃液体火箭发动机燃烧模型及计算机模拟

A COMBUSTION MODEL AND COMPUTER SIMULATION OF LOX/HYDROCARBON ROCKET ENGINES

关键词:  液氧  烃  液体推进剂火箭发动机  燃烧模拟

Key words:  Liquid oxygen  Hydrocarbon  Liquid rocket engine  Combustion  Simulation

摘要:

本文提出了一个通用的液氧/烃液体火箭发动机燃烧模型.模型采用多流管压力耦合方法,并考虑了推进剂液滴剥离、高压超临界燃烧和液膜冷却等对发动机燃烧过程的影响.利用本模型对液氧/丙烷发动机燃烧过程的计算模拟表明:本模型为液氧/烃发动机燃烧过程的模拟和性能预估提供了一个有效的理论工具.

Abstract:

A current mold el of combustion in LOX/hydrocarbon rocket engines is presented.Combustion processes are described with coupled stream tube mode. Specially,the effects of stripping of propellant droplets,supercritical combustion, and filmcooling on combustion are considered. With the model, the combustion processes in LOX/propane engines are simulated. The results show that the model provides an efficient method for simulation of combustion processes in LOX/ hydrocarbon rocket engines and for prediction of performance.