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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：US20240102418A1
公开(公告)日：2024-03-28
申请号：US18459716
申请日：2023-09-01
申请人： RTX CORPORATION
CPC分类号： F02C6/18 , F02C7/32 , F02C9/18 , F05D2220/62 , F05D2260/10 , F05D2260/213 , F05D2260/232
摘要： A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger, and expanded through a power turbine that is coupled to drive the auxiliary compressor section.
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公开(公告)号：US12098676B1
公开(公告)日：2024-09-24
申请号：US18238669
申请日：2023-08-28
申请人： RTX CORPORATION
摘要： An aircraft propulsion system includes a core engine for generating an exhaust gas flow that is expanded through a turbine to generate shaft power. A heat exchanger is in communication with a partial portion of the exhaust gas flow and an exit flow is emitted from the heat exchanger. An ejector is configured to increase a pressure of the exit flow with a motive flow taken from the core flow path.
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公开(公告)号：US12031481B2
公开(公告)日：2024-07-09
申请号：US18459716
申请日：2023-09-01
申请人： RTX CORPORATION
CPC分类号： F02C6/18 , F02C7/32 , F02C9/18 , F05D2220/62 , F05D2260/10 , F05D2260/213 , F05D2260/232
摘要： A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger, and expanded through a power turbine that is coupled to drive the auxiliary compressor section.
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