A gas turbine engine includes a core air passage, a combustor, and a steam line. The combustor is located in the core air passage and combusts hydrogen fuel to produce combustion gas. A steam line is fluidly coupled to the core air passage at a location downstream of the combustor to receive a portion of the combustion gas. A conduit thermally coupled to an exterior surface of the aircraft may be fluidly coupled to the steam line to receive combustion gases and heat the exterior surface. The gas turbine engine may also include a water vapor condenser fluidly connected to the steam line to receive the combustion gas and condense water vapor of the combustion gas. At least one nozzle may be fluidly coupled to the water vapor condenser to spray condensed water into the core air passage.
一种燃气涡轮发动机,包括核心空气通道、燃烧器和蒸汽管线。燃烧器位于核心空气通道中并燃烧氢燃料,产生燃烧气体。蒸汽管线在燃烧器的下游的位置处流体地联接到核心空气通道,以接收燃烧气体的一部分。热联接到飞行器的外部表面的管道可流体地联接到蒸汽管线以接收燃烧气体并加热外部表面。燃气涡轮发动机还可包括水蒸气冷凝器,水蒸气冷凝器流体地连接到蒸汽管线以接收燃烧气体并冷凝燃烧气体的水蒸气。至少一个喷嘴可流体地联接到水蒸汽冷凝器以将冷凝水喷射到核心空气通道中。
Ice protection system for hydrogen-fueled aircraft
用于以氢为燃料的飞行器的防冰系统
2024-03-05
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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Hydrogen-fueled subsonic aircraft: A perspective
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