发明授权
US4809512A Air-fuel injection system for a turbojet engine 失效
涡轮喷气发动机的空气燃料喷射系统

Air-fuel injection system for a turbojet engine
摘要:
An improved swirler system for a turbojet engine combustion chamber is disclosed in which stationary first vanes and moveable second vanes are oriented at different angles with respect to a radius of the fuel injector system. The different angles allow the angle of the incoming air to be adjusted between full power and idle conditions so as to vary the conial shape of the atomized air-fuel mixture according to the operating conditions of the engine. Radial and axial inlet duct portions serve to attenuate the wakes of the air flow generated by the vanes prior to the air passing into the combustion chamber.
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