关键词: 燃气发生器；燃烧室出口喉道；离心喷嘴；进气道喘振；富油燃气；双燃烧室冲压发动机

Abstract: Gas generator can solve the difficulty of ignition and steady combustion of liquid kerosene in a supersonic combustor under the conditions of low Mach number and total temperature. In order to provide references to the design of gas generator and the ways of forced ignition in low Mach number free stream，wind tunnel experiments have been carried out to study the influences of the combustor construction，kerosene injection schemes and combustion organization under the free stream Mach 6 and total temperature 1650K. The experimental results show that，with the decreasing of combustor throat，combustor wall pressure increase and the disturbance zone in isolator moves upstream for both cold and combustion cases. When [QS]=0.50 (combustor exit area/isolate exit area)，inlet can start for cold case but buzz for combustion case. When [QS]=0.78 and 1.12，inlet can start for both cold and combustion cases. When [QS]=0.78 and kerosene/air ratio is 11 with two injection position，success in ignition and steady combustion are obtained，the inlet can start and gas generator can produce high temperature and rich fuel gas. Kerosene injected from swirl nozzle with low driving pressure and large injector can be ignited much easier and results in much better combustion efficiency. There exists a maximum of kerosene addition under the rich fuel gas condition which can be used to control the gas temperature by increase or decrease the kerosene injection mass.

Key words: Gas generator；Combustor exit throat；Swirl nozzle；Inlet buzzing；Rich fuel gas；Dual combustor ramjet