The invention discloses a turboshaft engine, an aircraft and a method. The problem that a traditional turboshaft engine cannot meet reasonable matching of plateau takeoff power and sea level takeoff power at the same time is solved. A turboshaft engine comprises an air inlet pipe, a driving mechanism, an impeller, a rotating shaft, an air compressor, an air compressor rotating shaft, a rotor brake mechanism, a clutch, a combustion chamber, a turbine assembly and an exhaust nozzle, the driving mechanism is arranged at the output end of the rotating shaft, the impeller is electrically connected with the driving mechanism, the impeller and the rotor brake mechanism are arranged at the output end of the rotating shaft, and the air compressor is arranged on the air compressor rotating shaft. The clutch sleeves the rotating shaft and is arranged between the rotating shaft and the compressor rotating shaft, and the turbine assembly is arranged at the driving end of the rotating shaft. The turboshaft engine, the aircraft and the method are used for being matched with the take-off power of the aircraft under different working conditions.
本发明公开一种涡轴发动机、飞行器及方法,以解决传统涡轴发动机无法同时满足高原起飞功率与海平面起飞功率合理匹配的问题。涡轴发动机,包括进气管、驱动机构、叶轮、转轴、压气机、压气机转轴、转子刹车机构、离合器、燃烧室、涡轮组件以及尾喷管,驱动机构设在转轴的输出端,叶轮与驱动机构电连接,叶轮和转子刹车机构设在转轴的输出端,压气机设在压气机转轴上,离合器套设在转轴上,离合器设在转轴与压气机转轴之间,涡轮组件设在转轴的驱动端。本发明提供的涡轴发动机、飞行器及方法用于匹配飞行器在不同工况下的起飞功率。
Turboshaft engine, aircraft and method
一种涡轴发动机、飞行器及方法
2024-03-08
Patent
Electronic Resource
Chinese
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