膨胀循环氢氧发动机火炬点火系统方案研究  

Study on Torch Ignition Scheme for Expander Cycle LOX/LH_(2) Engine

作　　者：李锦江[1,2] 刘恒 刘登丰[1] 褚宝鑫[1] 张楠[1] LI Jinjiang;LIU Heng;LIU Dengfeng;CHU Baoxin;ZHANG Nan(Beijing Aerospace Propulsion Institute,Beijing,100076;Cryogenic Liquid Propulsion Technology Laboratory of China Aerospace Science and Technology Corporation,Beijing,100076)

机构地区：[1]北京航天动力研究所,北京100076 [2]中国航天科技集团有限公司低温液体推进技术实验室,北京100076

出　　处：《导弹与航天运载技术（中英文）》2024年第3期38-44,共7页Missiles and Space Vehicles

基　　金：民用航天技术预先研究项目(050106)。

摘　　要：针对膨胀循环氢氧发动机多次点火需求,开展了火炬式电点火系统方案论证和仿真研究,明确了较为合理的低压火炬式电点火系统方案,并完成整机级试验验证。结果表明,氢主阀打开瞬间点火室混合比波动较大,可能造成结构烧蚀;从氢涡轮前引气氢、氧泵后引液氧的方案烧蚀风险较小,但对发动机起动和稳态特性有一定影响。试验验证了仿真分析结果,实现了中国液体火箭发动机首次低压火炬式电点火起动,初步表明点火系统方案可行。In response to the multiple ignition requirement of the expander cycle hydrogen-oxygen engine,research on the torch ignition system scheme is conducted,and a relatively reasonable low-pressure torch ignition system scheme is identified.The results show that the mixing ratio of the torch igniter fluctuated greatly when opening the hydrogen main valve,which may cause structural ablation.The scheme of introducing hydrogen from the inlet of the hydrogen turbine and liquid oxygen from the outlet of the liquid oxygen pump has a lower ablation risk,but it has a certain impact on the engine's start-up and steady-state characteristics.The low-pressure torch ignition start-up tests of liquid rocket engine are carried out for the first time in China.The experimental results verify the simulation results,and indicating the feasibility of the scheme.

关 键 词：膨胀循环 氢氧发动机 火炬式电点火 系统方案 仿真 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]