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公开(公告)号：US20240084731A1
公开(公告)日：2024-03-14
申请号：US18242699
申请日：2023-09-06
申请人： RTX CORPORATION
发明人： Alan Retersdorf , Stephen H. Taylor , Nathan A. Snape , Oliver V. Atassi , Malcolm P. MacDonald
CPC分类号： F02C6/08 , F02C7/14 , F02C9/18 , F05D2220/60 , F05D2260/213
摘要： A gas turbine engine assembly includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate an exhaust gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section through an engine drive shaft. A tap is at a location up stream of the combustor section for drawing a bleed airflow. A bleed air heat exchanger places the bleed airflow in thermal communication with an auxiliary flow for heating the bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow.
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公开(公告)号：US20240167427A1
公开(公告)日：2024-05-23
申请号：US18425131
申请日：2024-01-29
申请人： RTX CORPORATION
摘要： A propulsion system for an aircraft includes a core engine that includes a core flow path where a core flow is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen-based fuel, and ignited to generate a gas flow that is expanded through a turbine section. A fuel system is configured to supply a hydrogen based fuel to the combustor through a fuel flow path. A condenser is arranged along the core flow path and configured to extract water from the gas flow. An intercooling system receives a portion of water from the condenser for cooling a portion of the core flow at a first location within the compressor section. Heated water from the intercooling system is exhausted to a second location within the core flow path downstream of the first location.
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