全流量补燃循环试验发动机启动过程  

Start-up in a subscale full flow staged combustion cycle engine

作　　者：汪小卫[1] 金平[1] 张国舟[1] 俞南嘉[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《推进技术》2008年第4期407-411,共5页Journal of Propulsion Technology

摘　　要：分析了全流量补燃循环发动机系统启动过程难点,针对全流量补燃循环缩尺发动机热试车启动过程,分别就发动机中富燃/富氧预燃室的自身启动和相对启动过程进行了设计;采用管路-体积组合模块化方法,建立了发动机启动过程仿真模型,进行了仿真计算。按设计启动方案进行了多次热试车,试车结果表明发动机点火可靠,启动过程平稳,无烧蚀现象,且仿真结果很好地预示了热试车情况。In order to develop full flow staged combustion cycle engine （FFSC） technology, the starting process of a HE/OEsubscale full-flow staged combustion cycle engine was studied. The characteristics of the full-flow cycle were described, and the design difficulties of starting process of this cycle were discussed in two points： the start-up of oxidizer-rich/fuel-rich preburners and relative timing control for them. A special start-up program for the subscale hot-fire test was presented. Modu-larization simulation codes based on a pipe-volume module disassembly method were developed to study the accurate start-up time interval, and simulation mathematical models of some typical components were presented. With application of the start-up program, stable operation and non-ablation were demonstrated in several hot-fire tests, and the results of simulation are consistent with those of tests.

关 键 词：液体推进剂火箭发动机 全流量补燃循环+ 起动试验 动态模型 仿真模型 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]