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公开(公告)号：US20230399984A1
公开(公告)日：2023-12-14
申请号：US18239314
申请日：2023-08-29
Applicant: ROLLS-ROYCE PLC
Inventor： Mark SPRUCE
CPC classification number: F02C7/36 , F02C6/20 , F16C17/03 , F16H1/28 , F16H57/02 , F16H57/08 , F16C2360/23 , F16H2057/02043 , F16H2057/085
Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines, including 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.
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公开(公告)号：US20220307426A1
公开(公告)日：2022-09-29
申请号：US17576218
申请日：2022-01-14
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that can receive an input from the core shaft, and can output drive to a fan shaft via an output of the gearbox so as to drive the fan at a lower rotational speed than the core shaft; and a fan shaft mounting structure arranged to mount the fan shaft within the engine, the fan shaft mounting structure including at least two supporting bearings connected to the fan shaft. A fan-gearbox axial distance is defined as the axial distance between the output of the gearbox and the fan axial centreline, the fan-gearbox axial distance being greater than or equal to 0.35 m.
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公开(公告)号：US20210372329A1
公开(公告)日：2021-12-02
申请号：US17404420
申请日：2021-08-17
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: An engine for an aircraft includes an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox. The gearbox is an epicyclic gearbox and comprises a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The radial bending stiffness of the planet carrier is equal to or greater than 1.20×109 N/m, and/or the tilt stiffness of the planet carrier is greater than or equal to 6.00×108 Nm/rad. A method of operation of such an engine is also disclosed.
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公开(公告)号：US20210310419A1
公开(公告)日：2021-10-07
申请号：US17197311
申请日：2021-03-10
Applicant: ROLLS-ROYCE PLC
Inventor： Mark SPRUCE
Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: 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.
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公开(公告)号：US20210310416A1
公开(公告)日：2021-10-07
申请号：US16995901
申请日：2020-08-18
Applicant: ROLLS-ROYCE PLC
Inventor： Mark SPRUCE
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20210310373A1
公开(公告)日：2021-10-07
申请号：US17205870
申请日：2021-03-18
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: 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.
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公开(公告)号：US20210254555A1
公开(公告)日：2021-08-19
申请号：US17244208
申请日：2021-04-29
Applicant: ROLLS-ROYCE PLC
Inventor： Mark SPRUCE
Abstract: An engine for an aircraft has an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from a gearbox input shaft portion of the core shaft and to output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, a plurality of planet gears, a ring gear, and a planet carrier. The planet carrier and the gearbox support each have a torsional stiffness, and a carrier to gearbox support torsional stiffness ratio is greater than or equal to 2.3.
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公开(公告)号：US20210172381A1
公开(公告)日：2021-06-10
申请号：US17066713
申请日：2020-10-09
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that can receive an input from the core shaft, and can output drive to a fan shaft via an output of the gearbox so as to drive the fan at a lower rotational speed than the core shaft; and a fan shaft mounting structure arranged to mount the fan shaft within the engine, the fan shaft mounting structure including at least two supporting bearings connected to the fan shaft. A fan-gearbox axial distance is defined as the axial distance between the output of the gearbox and the fan axial centreline, the fan-gearbox axial distance being greater than or equal to 0.35 m.
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公开(公告)号：US20210172377A1
公开(公告)日：2021-06-10
申请号：US16807737
申请日：2020-03-03
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: Gas turbine engine for aircraft including: engine core including turbine, compressor, and core shaft connecting turbine to compressor; fan located upstream of engine core, including plurality of fan blades; gearbox receives input from core shaft and outputs drive to fan shaft to drive fan at lower rotational speed than core shaft; and fan shaft mounting structure arranged to mount fan shaft within engine. Fan shaft mounting structure includes at least two supporting bearings connected to fan shaft. Gearbox's output is at gearbox output position and fan's input is at fan input position. First bearing separation distance is defined as axial distance between input to fan and closest bearing of at least two supporting bearings in rearward direction from fan. First bearing separation ratio of: the first bearing separation distance ( d 1 ) the axial distance between the fan input position and the gearbox output position ( d 4 ) is greater than or equal to 1.6×10−1, and the axial distance between the fan input position and the gearbox output position (d4) is greater than or equal to 0.43 m.
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公开(公告)号：US20190162292A1
公开(公告)日：2019-05-30
申请号：US16198172
申请日：2018-11-21
Applicant: Rolls-Royce Deutschland Ltd & Co KG , Rolls-Royce plc
Inventor： Michael NIQUE , Paul GORENZ , Christopher CAMPBELL , Frank WAGNER , Mark SPRUCE , Daren ASHMORE
Abstract: A planetary gearing includes a sun gear rotating about a rotation axis and driven by a sun shaft; planet gears driven by the sun gear, each planet gear having an axially forward face side and an axially rearward face side; a ring gear engaging the planet gears; and planet slide bearing pins, wherein respectively one planet slide bearing pin is arranged inside a planet gear forming a lubricated journal bearing. At an axially forward face side and/or axially rearward face side, each planet gear forms a recess that extends inside the planet gear starting from the face side, and the planet slide bearing pins respectively form one crowning at their abutment surface such that their outer diameter decreases from a maximum outer diameter to at least an axial end of the abutment surface and has a minimum at the axial end.
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