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公开(公告)号：EP4407158A2
公开(公告)日：2024-07-31
申请号：EP24182311.1
申请日：2023-05-18
申请人： RTX Corporation
IPC分类号： F02C3/107
CPC分类号： F02C7/36 , F05D2220/7620130101 , F02C7/32 , F01D15/10 , F02C3/107 , F05D2260/4220130101
摘要： A power extraction system (100) for a gas turbine engine (20) may comprise a low spool transmission (72) and a low spool accessory gearbox (70). The low spool accessory gearbox may comprise a generator (76) and a dual clutch transmission. The dual clutch transmission may be coupled between the low spool transmission and the generator.
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公开(公告)号：EP4345007A3
公开(公告)日：2024-07-31
申请号：EP23195512.1
申请日：2023-09-05
申请人： RTX Corporation
发明人： HANRAHAN, Paul R.
CPC分类号： F02C7/36 , B64D35/04 , B64C27/12 , F02C3/113 , F05D2260/4031120130101
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a carrier (90), a first gear system (86), a second gear system (88) and a lock device (106). The first gear system (88) includes a sun gear (92), a first ring gear (94) and a plurality of first intermediate gears (96) between and meshed with the sun gear (92) and the first ring gear (94). Each of the first intermediate gears (96) is rotatably mounted to the carrier (90). The second gear system (88) includes a second ring gear (102) and a plurality of second intermediate gears (104) meshed with the second ring gear (102). Each of the second intermediate gears (104) is rotatably mounted to the carrier (90). The lock device (106) is configured to lock rotation of the carrier (90) about an axis (28) during a first mode. The lock device (106) is configured to unlock rotation of the carrier (90) about the axis (28) during a second mode.
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公开(公告)号：EP4283106A1
公开(公告)日：2023-11-29
申请号：EP23175819.4
申请日：2023-05-26
申请人： RTX Corporation
发明人： HANRAHAN, Paul R.
摘要： An assembly (20) is provided for an aircraft. The aircraft assembly (20) includes a rotating structure (68), a geartrain (78), a propulsor rotor (24) and an electric machine (80). The rotating structure (68) includes a turbine rotor (60). The geartrain (78) includes a sun gear (92), a ring gear (94), a plurality of intermediate gears (96) and a carrier (98). The sun gear (92) is rotatably driven by the rotating structure (68). Each of the intermediate gears (96) is between and meshed with the sun gear (92) and the ring gear (94). Each of the intermediate gears (96) is rotatably mounted to the carrier (98). The propulsor rotor (24) is rotatably driven by the carrier (98). The electric machine (80) is coupled to the ring gear (94).
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公开(公告)号：EP4273390A3
公开(公告)日：2023-11-15
申请号：EP23171720.8
申请日：2023-05-04
申请人： RTX Corporation
摘要： A gas turbine engine (10) includes a first spool (16), a second spool (12), a third spool (14), and an epicyclic differential. The epicyclic differential includes a sun gear, planet gears supported from a planet carrier, a ring gear, and a locking member, each housed within an accessory gearbox. The planet carrier couples to the second spool (12). The sun gear couples to the third spool (14), and the ring gear couples to engine accessories. A method of operating the gas turbine engine (10) includes supplying a first fuel flow (58) rate to a primary combustor (70) associated with the first (16) and third (14) spools and supplying a second fuel flow (58) rate to a secondary combustor (84) associated with the second spool (12) based on a power lever angle within an intermediate power level range.
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公开(公告)号：EP4365426A1
公开(公告)日：2024-05-08
申请号：EP23207768.5
申请日：2023-11-03
申请人： RTX Corporation
IPC分类号： F02C3/13 , F02C6/02 , F02C6/06 , F02C6/08 , F02C9/42 , F02K3/075 , F02K3/077 , F02C9/18 , F02K3/12
CPC分类号： F02C6/06 , F02C6/08 , F02C3/13 , F02K3/075 , F02K3/077 , F02C9/42 , F02C6/02 , F02C9/18 , F02K3/12
摘要： A powerplant (20) for an aircraft includes a first gas turbine engine (28), a second gas turbine engine (30), a second engine bypass flowpath (84) and a flow control system (34). The first gas turbine engine (28) includes a first core flowpath (44) fluidly coupled with a first inlet (58) and a first exhaust (60). The first core flowpath (44) extends sequentially through a first compressor section (37), a first combustor section (38) and a first turbine section (39). The second gas turbine engine (30) includes a second core flowpath (82) fluidly coupled with a second inlet (94) and a second exhaust (96). The second core flowpath (82) extends sequentially through a second compressor section (76), a second combustor section (77) and a second turbine section (78). The flow control system (34) fluidly couples the first inlet (58) and the first exhaust (60) to the second core flowpath (82) during a first mode. The flow control system (34) fluidly couples the first inlet (58) and the first exhaust (60) to the second engine bypass flowpath (84) during a second mode.
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公开(公告)号：EP4336026A1
公开(公告)日：2024-03-13
申请号：EP23195543.6
申请日：2023-09-05
申请人： RTX Corporation
发明人： HANRAHAN, Paul R.
IPC分类号： F02C3/113 , F02C3/13 , F02C6/08 , F02C6/20 , F02C7/36 , F02K3/06 , B64C29/00 , B64D35/04 , F16H48/22
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a compressor section (46), a combustor section (47), a turbine section (48) and a flowpath (112) extending sequentially through the compressor section (46), the combustor section (47) and the turbine section (48). The assembly also includes a turbine rotor (60), a propulsor rotor (22) and an auxiliary turbine (138). The turbine rotor (60) is within the turbine section (48). The turbine rotor (60) is configured to rotatably drive the propulsor rotor (22). The auxiliary turbine (138) includes an auxiliary turbine rotor (148). The auxiliary turbine rotor (148) is configured to rotatably drive the propulsor rotor (22) with the turbine rotor (60). The auxiliary turbine (138) is configured to receive bleed gas from the flowpath (112).
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公开(公告)号：EP4325087A1
公开(公告)日：2024-02-21
申请号：EP23191414.4
申请日：2023-08-14
申请人： RTX Corporation
摘要： An assembly for an aircraft includes a geartrain (72), a first propulsor rotor (22) and a rotating structure (68). The geartrain (72) includes a sun gear (92), a ring gear (94), a plurality of intermediate gears (96) and a carrier (98). The ring gear (94) circumscribes the sun gear (92) and is rotatable about an axis (28, 40, 100). Each of the intermediate gears (96) is between and meshed with the sun gear (92) and the ring gear (94). Each of the intermediate gears (96) is rotatably mounted to the carrier (98). The carrier (98) is rotatable about the axis (28, 40, 100). The first propulsor rotor (22) is coupled to the carrier (98). The rotating structure (68) is coupled to the ring gear (94). The rotating structure (68) includes a turbine rotor (60). The rotating structure (68) is configured to drive rotation of the first propulsor rotor (22) through the geartrain (72).
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公开(公告)号：EP4325031A1
公开(公告)日：2024-02-21
申请号：EP23191746.9
申请日：2023-08-16
申请人： RTX Corporation
发明人： HANRAHAN, Paul R.
摘要： An assembly for an aircraft propulsion system (20) includes a compressor section (48), a combustor section (49), a turbine section (50) and a flowpath (110) extending sequentially through the compressor section (48), the combustor section (49) and the turbine section (50). The assembly also includes a rotating structure (78), a geartrain (82), a propulsor rotor (24) and a turbine (84). The rotating structure (78) includes a turbine rotor (69) within the turbine section (50). The geartrain (82) is coupled to the rotating structure (78). The propulsor rotor (24) is coupled to the geartrain (82). The rotating structure (78) is configured to drive rotation of the propulsor rotor (24) through the geartrain (82). The turbine (84) is coupled to the geartrain (82). The turbine (84) is configured to receive bleed gas from the flowpath (110).
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公开(公告)号：EP4282763A1
公开(公告)日：2023-11-29
申请号：EP23175773.3
申请日：2023-05-26
申请人： RTX Corporation
发明人： HANRAHAN, Paul R.
IPC分类号： B64D27/24
摘要： An assembly for an aircraft includes a carrier (90), a first gear system (86), a second gear system (88) and an idler gear (92). The first gear system (86) includes a first sun gear (94), a first ring gear (96) and a plurality of first intermediate gears (98). Each of the first intermediate gears (98) is between and is meshed with the first sun gear (94) and the first ring gear (96). Each of the first intermediate gears (98) is rotatably mounted to the carrier (90). The second gear system (88) includes a second sun gear (104), a second ring gear (106) and a plurality of second intermediate gears (108). Each of the second intermediate gears (108) is between and is meshed with the second sun gear (104) and the second ring gear (106). Each of the second intermediate gears (108) is rotatably mounted to the carrier (90). The idler gear (92) couples the first ring gear (86) to the second ring gear (88).
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公开(公告)号：EP4273385A1
公开(公告)日：2023-11-08
申请号：EP23171722.4
申请日：2023-05-04
申请人： RTX Corporation
摘要： A gas turbine engine (10) includes a first spool (16) of a primary flow path (216) and a second spool (12) of a secondary flow path (220). The second spool (12) is nonconcentric with the first spool (16). The second spool (12) includes a boost compressor (96) and a load compressor (104) in fluid communication with an inlet plenum (128). An inlet duct assembly (62) and an outlet duct assembly (130) place the secondary flow path (220) in communication with the primary flow path (216). The gas turbine (100) includes a controller operable to vary open areas of variable inlet guide vanes to control a flow division between the boost compressor (96) and the load compressor (104).
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