全流量补燃循环试验发动机启动过程

推进技术 ›› 2008, Vol. 29 ›› Issue (4): 407-411.

全流量补燃循环试验发动机启动过程

汪小卫,金平,张国舟,俞南嘉,蔡国飙

北京航空航天大学宇航学院;北京航空航天大学宇航学院;北京航空航天大学宇航学院;北京航空航天大学宇航学院;北京航空航天大学宇航学院

发布日期:2021-08-15

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

School of Astronautics,Beijing Univ.of Aeronauties and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronauties and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronauties and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronauties and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronauties and Astronautics,Beijing 100083,China

Published:2021-08-15

摘要/Abstract

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。

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

Abstract: In order to develop full flow staged combustion cycle engine(FFSC) technology,the starting process of a H2/O2 subscale 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.Modularization 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.

Key words: Liquid propellant rocket engine;Full flow staged combustion cycle+;Starting test;Dynamic model;Simulation model

汪小卫,金平,张国舟,俞南嘉,蔡国飙. 全流量补燃循环试验发动机启动过程[J]. 推进技术, 2008, 29(4): 407-411.