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补燃循环发动机起动过程涡轮功率控制
引用本文:徐浩海,刘站国.补燃循环发动机起动过程涡轮功率控制[J].火箭推进,2006,32(4):10-14.
作者姓名:徐浩海  刘站国
作者单位:西安航天动力研究所,陕西,西安,710100
摘    要:分析了采用富氧燃气发生器的补燃循环发动机起动过程中涡轮功率的控制方法,指出起动过程中涡轮功率的主要控制参数为发生器温度和涡轮压比。起动过程中发生器温度的控制依靠选择合适的流量调节器起动流量、转级时间和转级速率来实现。起动过程中涡轮压比的控制需要控制推力室的建压时间和建压幅度,这需要选择合适的推力室燃料主阀打开时间、燃料节流阀转大流量的时间。通过数值仿真,分析了上述控制方法对发动机起动过程的影响机理。

关 键 词:液体火箭发动机  补燃循环  起动  功率控制
文章编号:(2006)04-0010-05
收稿时间:2006-04-03
修稿时间:2006-05-25

Turbine power control of staged combustion cycle engine during start-up
Xu Haohai,Liu Zhanguo.Turbine power control of staged combustion cycle engine during start-up[J].Journal of Rocket Propulsion,2006,32(4):10-14.
Authors:Xu Haohai  Liu Zhanguo
Abstract:The approach to control the turbine power during engine start-up for staged combustion cycle engine using an oxidant rich gas generator is described in this paper. The primary parameters which control turbine power are GG temperature and turbine pressure ratio. The GG temperature control can be realized by regulating the flow regulator start-up flow rate, the start time from start-up to main stage and the regulator operating condition transfer rate. By choosing the main fuel valve opening time and the mixture ratio control valve (MRV) conversion time to larger mass flow, the combustion chamber ignition time and the peak value of chamber pressure are controlled. By this method, the turbine pressure ratio can be controlled during engine start-up process. The influence of the above methods on start-up characteristic is analyzed by numerical simulation.
Keywords:liquid rocket engine  staged combustion cycle engine  start-up  power control
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