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公开(公告)号：EP4411128A2
公开(公告)日：2024-08-07
申请号：EP24184479.4
申请日：2016-02-08
申请人： RTX Corporation
IPC分类号： F02K1/76
摘要： An integrated propulsion system (10) comprises components that include a gas turbine engine (20) and a nacelle assembly (82). The nacelle assembly (82) includes a fan nacelle (86) arranged at least partially about a fan (42) and an engine. The system includes a fan section (22) at least partially defined by the fan nacelle (82), and the fan section (22) has a fan pressure ratio of less than about 1.7. The engine includes a turbine section (28) configured to drive the fan section (22) and a compressor section (24), the compressor section (24) including a first compressor (44) and a second compressor (52). An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor (44) and a pressure ratio across the second compressor (52), and wherein the overall pressure ratio is greater than or equal to about 35. The fan section (22) is configured to deliver a portion of air into the compressor section (24), and a portion of air into a bypass duct, and wherein a bypass ratio, defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section (24), is equal to or greater than about 5.
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公开(公告)号：EP4411128A3
公开(公告)日：2024-10-09
申请号：EP24184479.4
申请日：2016-02-08
申请人： RTX Corporation
摘要： An integrated propulsion system (10) comprises components that include a gas turbine engine (20) and a nacelle assembly (82). The nacelle assembly (82) includes a fan nacelle (86) arranged at least partially about a fan (42) and an engine. The system includes a fan section (22) at least partially defined by the fan nacelle (82), and the fan section (22) has a fan pressure ratio of less than about 1.7. The engine includes a turbine section (28) configured to drive the fan section (22) and a compressor section (24), the compressor section (24) including a first compressor (44) and a second compressor (52). An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor (44) and a pressure ratio across the second compressor (52), and wherein the overall pressure ratio is greater than or equal to about 35. The fan section (22) is configured to deliver a portion of air into the compressor section (24), and a portion of air into a bypass duct, and wherein a bypass ratio, defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section (24), is equal to or greater than about 5.
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公开(公告)号：EP4310302A1
公开(公告)日：2024-01-24
申请号：EP23187374.6
申请日：2023-07-24
申请人： RTX Corporation
摘要： An aircraft system (20) includes a gas turbine engine (22), a gearbox (26) and at least one compressor (24). The gas turbine engine (22) includes a compressor section (32), a turbine section (36), a combustor section (34) and a rotating structure (50). The combustor section (34) is fluidly coupled with and between the compressor section (32) and the turbine section (36). The rotating structure (50) includes a compressor section rotor (44) within the compressor section (32) and a turbine section rotor (46) within the turbine section (36). The at least one compressor (24) includes a compressor rotor (54) rotatably driven by the rotating structure (50) through the gearbox (26). The gas turbine engine (22) may be dedicated to powering the at least one compressor (24).
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