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公开(公告)号：EP4407158A3
公开(公告)日：2024-10-02
申请号：EP24182311.1
申请日：2023-05-18
申请人： RTX Corporation
CPC分类号： F02C7/36 , F05D2220/7620130101 , F02C7/32 , F01D15/10 , F02C3/107 , F05D2260/4220130101 , F05D2270/30320130101
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：EP4435297A2
公开(公告)日：2024-09-25
申请号：EP24193816.6
申请日：2021-01-18
申请人： RTX Corporation
发明人： JABIDO, Janice , McCUNE, Michael E.
IPC分类号： F16H57/04
CPC分类号： F02C7/06 , F02C7/36 , F05D2260/4031120130101 , F05D2240/12620130101 , F16H57/0482 , F16H57/0423
摘要： A fan drive gear system (55) for a turbofan engine (20) according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear (72) that is rotatable about an axis (A), a plurality of intermediate gears (74) driven by the sun gear (72), and a baffle (80) that is disposed between at least two of the plurality of intermediate gears (74) for defining a lubricant flow path from an interface between the sun gear (72) and at least one of the plurality of intermediate gears (74). The baffle (80) includes a channel (96) with at least one ramp portion (108, 110) directing lubricant.
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公开(公告)号：EP3885551B1
公开(公告)日：2024-08-28
申请号：EP21152583.7
申请日：2021-01-20
CPC分类号： F02C3/10 , F02C3/13 , F02K3/06 , F02K5/00 , F02C6/00 , F02C6/20 , F02C6/206 , F05D2220/7620130101 , F05D2220/32320130101 , F05D2260/4031120130101 , F02C7/36
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公开(公告)号：EP3872328B1
公开(公告)日：2024-08-28
申请号：EP21170270.9
申请日：2018-01-29
CPC分类号： F16H57/04 , F16H57/0426 , F02C7/36 , F16H57/08 , F16H2057/08520130101
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公开(公告)号：EP4407159A2
公开(公告)日：2024-07-31
申请号：EP24182404.4
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：EP3885562B1
公开(公告)日：2024-07-17
申请号：EP18940576.4
申请日：2018-11-19
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公开(公告)号：EP4390107A1
公开(公告)日：2024-06-26
申请号：EP23218820.1
申请日：2023-12-20
申请人： RTX Corporation
CPC分类号： F02K3/062 , F02C7/36 , F05D2260/4031120130101 , F02C3/10
摘要： A fan drive turbine (112) drives a drive shaft (114). A compressor section and a turbine section rotate about a rotational axis, with the turbine section positioned in a downstream direction. A fan has fan blades (102) and a fan hub (103) positioned radially within a fan case (104), with the fan case (104) defining a bypass duct (105). A fan inlet guide vane case (106) is upstream of the fan blades (102) and a fan exit guide vane case (108) is mounted downstream. The drive shaft (114) is mounted on at least one input drive shaft bearing (116) inwardly of the fan inlet guide vane case (106). The drive shaft (114) drives a flexible coupling (120) to in turn drive a gear reduction (122). The gear reduction (122) drives a fan drive shaft (124) to in turn drive the fan hub (103). At least two fan drive shaft bearings (128, 130) support the fan drive shaft (124) within the fan exit guide vane case (108).
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公开(公告)号：EP2948633B1
公开(公告)日：2024-05-22
申请号：EP13786820.4
申请日：2013-10-23
CPC分类号： B64C11/46 , F02K3/025 , F02C6/206 , F05B2240/1220130101 , F05B2260/9620130101 , F05D2220/32520130101 , F05D2250/3020130101 , F05D2260/1420130101 , F05D2220/32420130101 , F05D2250/5220130101 , F02K1/46 , F05D2250/5120130101 , B64C11/18 , Y02E10/72 , B64C11/00 , F05D2260/4031120130101 , F02C7/36 , F05D2250/7020130101 , F05D2220/9020130101 , F05D2240/30120130101 , Y02T50/60
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公开(公告)号：EP4365425A1
公开(公告)日：2024-05-08
申请号：EP23207225.6
申请日：2023-10-31
摘要： A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R1 and a primary fan hub radius R2; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3 and a secondary fan hub radius R4, wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to %Fn3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ratio of R1 to R3 equals EFP1−RqRSec.−Fan21−RqRPrim.−Fan21%Fn3s−1; wherein EFP is between 1.5 and 11, wherein RqRPrim.-Fan is a ratio of R1 to R2, and wherein RqRSec.-Fan is a ratio of R3 to R4.
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