公开(公告)号：US20240318575A1

公开(公告)日：2024-09-26

申请号：US18186347

申请日：2023-03-20

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Kashif MOHAMMED ,  John SGOUROMITIS

IPC分类号： F01D21/14 ,  F01D25/18

CPC分类号： F01D21/14 ,  F01D25/18 ,  F05D2260/98

摘要： An aircraft engine, has: an oil system, a component containing a baseline volume of oil during normal operation greater than a maximum volume of the oil for compliance with fire resistance requirements, the oil system having: an oil circuit, a de-priming port fluidly connected to a fluid source at a pressure sufficient to overcome a pressure drop through the component to drain the component to a volume of oil less than the maximum volume of the oil for compliance with the fire resistance requirements, and a valve connected to the de-priming port, the valve having a closed configuration preventing the fluid from entering the oil circuit and an open configuration permitting the fluid to enter the oil circuit via the de-priming port and through the valve, the valve movable from the closed configuration to the open configuration in response to the component being subjected to a fire event.

公开(公告)号：US12025018B2

公开(公告)日：2024-07-02

申请号：US17766143

申请日：2020-09-30

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Catherine Pikovsky ,  Antoine Jean-Philippe Beaujard

IPC分类号： F01D25/18 ,  F01D25/16

CPC分类号： F01D25/18 ,  F01D25/162 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2260/98

摘要： A turbine arrangement comprising a journal having a flange carrying a disc that is attached to the flange with bolts, wherein it includes a stationary circular trough surrounding the flange for collecting oil capable of passing radially between the disc and the flange carrying this disc.

公开(公告)号：US20240200467A1

公开(公告)日：2024-06-20

申请号：US18588409

申请日：2024-02-27

申请人： ROLLS-ROYCE plc

发明人： Mark SPRUCE

IPC分类号： F01D25/18 ,  F01D25/16 ,  F02C3/113 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F16H57/04 ,  F16H57/08

CPC分类号： F01D25/18 ,  F01D25/166 ,  F02C3/113 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F16H57/0469 ,  F16H57/0479 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/40311 ,  F16H2057/085

摘要： Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

公开(公告)号：US11994257B2

公开(公告)日：2024-05-28

申请号：US15931032

申请日：2020-05-13

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Marion Daniel ,  Pierre Gauvin ,  Adam Logan

IPC分类号： F16N39/00 ,  B01D19/00 ,  F01D25/18

CPC分类号： F16N39/002 ,  B01D19/0052 ,  F01D25/18 ,  F05D2220/323 ,  F05D2260/609 ,  F05D2260/98 ,  F16N2210/02

摘要： A de-aerator for a lubrication system, has: a housing defining an air-oil inlet, an oil outlet, and an air outlet of the de-aerator; a rotor received within the housing and rotatable relative to the housing about a central axis, the rotor having blades distributed about the central axis and extending at least partially radially relative to the central axis, flow passages extending between the blades, the rotor having a hub circumferentially extending around the central axis and around the blades, the hub having a peripheral wall oriented radially inwardly and defining a fore opening leading to the flow passages; and a gap between the housing and the hub of the rotor, a portion of the housing received within the fore opening and axially overlapping the peripheral wall of the hub, the gap having a fore gap inlet between the portion of the housing and the peripheral wall of the hub.

公开(公告)号：US11965440B2

公开(公告)日：2024-04-23

申请号：US17257254

申请日：2019-07-05

申请人： SAFRAN

发明人： Arnaud Georges Nifenecker ,  Benjamin Nicolas Fulleringer ,  Cédric Jean Daniel Plaino ,  Xavier Roger Betbeder-Laüque

IPC分类号： B01D53/22 ,  B01D45/14 ,  F01D25/18 ,  F01M11/03 ,  F01M11/08 ,  F01M13/04 ,  F02C7/06

CPC分类号： F01M11/08 ,  B01D45/14 ,  F01D25/18 ,  F01M11/03 ,  F01M13/04 ,  F02C7/06 ,  F01M2013/0422 ,  F05D2220/32 ,  F05D2260/98

摘要： A part for a centrifugal breather for an air/oil mixture of a turbomachine is configured to rotate about a longitudinal axis of symmetry. The breather forms an annular chamber for centrifugal separation of said mixture. The chamber includes mesh structure that takes up at least one space in a duct which closes communication between an axial inlet and an internal radial outlet. The mesh structure is formed by the spatial repetition of the material or of the space of a single pattern produced by the interconnection of simple shapes. The pattern is designed such that the spaces between the materials paths passing through the materials in at least three dimensions of space forming a trihedron.

公开(公告)号：US11958623B2

公开(公告)日：2024-04-16

申请号：US17979393

申请日：2022-11-02

申请人： RTX Corporation

发明人： Gary D. Roberge

IPC分类号： B64D29/00 ,  B22F5/00 ,  B22F10/20 ,  B64D33/08 ,  F01D25/12 ,  F01D25/14 ,  F01D25/18 ,  F02K3/06 ,  F28D21/00 ,  B22F10/12 ,  B22F10/14 ,  B22F10/18 ,  B22F10/25 ,  B22F10/28

CPC分类号： B64D33/08 ,  B22F5/009 ,  B22F10/20 ,  B64D29/00 ,  F01D25/12 ,  F01D25/14 ,  F01D25/18 ,  F02K3/06 ,  B22F10/12 ,  B22F10/14 ,  B22F10/18 ,  B22F10/25 ,  B22F10/28 ,  F05D2230/22 ,  F05D2260/213 ,  F05D2260/22141 ,  F28D2021/0026

摘要： A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

公开(公告)号：US11946540B2

公开(公告)日：2024-04-02

申请号：US17895301

申请日：2022-08-25

申请人： RAYTHEON TECHNOLOGIES CORPORATION

发明人： Janice Jabido ,  Michael E. McCune

IPC分类号： F16H57/04 ,  F01D15/12 ,  F01D25/18 ,  F02K3/02 ,  F16H1/28 ,  F16H57/08

CPC分类号： F16H57/0427 ,  F01D15/12 ,  F01D25/18 ,  F02K3/025 ,  F16H1/28 ,  F16H57/0442 ,  F16H57/0479 ,  F16H57/0486 ,  F16H57/082

摘要： A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.

公开(公告)号：US11946380B2

公开(公告)日：2024-04-02

申请号：US17299889

申请日：2019-12-19

申请人： GKN Aerospace Sweden AB

发明人： Per Widstrom

IPC分类号： F01D25/18 ,  F01D25/12 ,  F16N39/02 ,  F28D21/00

CPC分类号： F01D25/18 ,  F01D25/125 ,  F16N39/02 ,  F05D2260/207 ,  F05D2260/232 ,  F16N2210/14 ,  F28D2021/0021

摘要： An aircraft engine circulation system comprises a conduit arranged in use to communicate a lubricant to and from one or more bearings of an engine. The conduits define a space which comprises a material that is selected to change phase at a predetermined temperature.

公开(公告)号：US11927262B2

公开(公告)日：2024-03-12

申请号：US17661869

申请日：2022-05-03

申请人： SAFRAN TRANSMISSION SYSTEMS

发明人： Bálint Pap ,  Patrice Jocelyn Francis Gedin ,  Antoine Jacques Marie Pennacino

IPC分类号： F16H57/04 ,  F01D25/18

CPC分类号： F16H57/0482 ,  F01D25/18 ,  F16H57/0427 ,  F16H57/0471 ,  F05D2260/40311

摘要： Lubrication device for a turbomachine reduction gear, the device comprising an annular lubricating oil collecting cup delimited by a first wall and a second wall, said cup being divided by internal walls extending between the first wall and the second wall so as to define a plurality of angular sectors forming oil collection basins, the basins being circumferentially adjacent around the axis and comprising lubricating oil outlets, characterized in that one or more of said internal walls have openings allowing oil to pass between the circumferentially adjacent basins, characterized in that said openings (58) are formed in one or more of said internal walls so as to define one or more rows of openings in said one or more internal walls.

公开(公告)号：US20240044289A1

公开(公告)日：2024-02-08

申请号：US18491888

申请日：2023-10-23

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Christophe Paul Jacquemard ,  Didier Gabriel Bertrand Desombre

IPC分类号： F02C7/06 ,  B64D27/02 ,  F01D25/18 ,  F16H57/04

CPC分类号： F02C7/06 ,  B64D27/02 ,  F01D25/18 ,  F16H57/045 ,  F05D2220/323 ,  F05D2260/98

摘要： An auxiliary tank for an aircraft turbine engine is provided, and in conjunction with a pump and associated auxiliary lubrication circuit, supplies oil to a reducer when, for example, a phase of free rotation of the fan is detected. Thus, the reducer is always lubricated, even during the phases of free rotation of the fan, thus ensuring a longer life of the reducer gears. The auxiliary tank is arranged with respect to the reducer so that oil is recovered from the reducer at least in part by the auxiliary tank.