富氧补燃循环发动机启动过程

Starting process of oxidizer-rich staged combustion rocket engine

关键词:  液体推进剂火箭发动机  加力燃烧  启动

Key words:  Liquid propellant rocket engine  Afterburning  Starting

摘要:

启动过程是液体火箭发动机研制中的重点和难点,解决大推力补燃循环发动机启动问题的主要措施应为:通过控制预燃室的燃料流量以有效地将预燃室的组元比控制在合理的范围内,并可以控制发动机的启动速率;燃烧室点火时预燃室应有较高的压力,同时应通过推力室燃料路的节流来减小燃烧室压力的上升速率;对于自身启动发动机,较高的入口压力有利于发动机启动。这些措施解决了富氧补燃循环发动机的启动问题,可供同类发动机的研制借鉴。

Abstract:

Start-up is the important and difficult aspect during liquid rocket engine development. The main ways to solve this problem of large thrust stage combustion engine are: control the mixture ratio of preburner in acceptable range by regulating the fuel flow rate in preburner, and control the acceleration time of engine during start-up; higher preburner pressure during combustion chamber ignition stage is necessary, at the same time acceleration of chamber pressure should be limited by setting throttle on combustion chamber fuel supply line. Higher inlet propellant pressure is helpful for self-start engine. These methods were applied to a stage combustion rocket engine to solve the problems, and will supply reference for the similar category engine development.