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公开(公告)号：US11643976B2
公开(公告)日：2023-05-09
申请号：US17966318
申请日：2022-10-14
Applicant: ROLLS-ROYCE PLC
Inventor： Mark Spruce
CPC classification number: F02C7/36 , F16H57/082 , F05D2200/14 , F05D2220/323 , F05D2260/40311 , F05D2300/501 , F16H2057/02043
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：US11512648B2
公开(公告)日：2022-11-29
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：US11268452B2
公开(公告)日：2022-03-08
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：US11022046B1
公开(公告)日：2021-06-01
申请号：US17161004
申请日：2021-01-28
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 for an aircraft is arranged to receive an input from a core shaft and to output drive to a 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 having a plurality of pins, each pin being arranged to have a planet gear of the plurality of planet gears mounted thereon. A ratio of planet carrier torsional stiffness to pin stiffness is within a specified range.
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公开(公告)号：US10830154B1
公开(公告)日：2020-11-10
申请号：US16807786
申请日：2020-03-03
Applicant: ROLLS-ROYCE PLC
Inventor： Mark Spruce
Abstract: A gas turbine engine includes: an engine core with a turbine, compressor, and core shaft; a fan upstream the engine core; a gearbox that can receive an input from the core shaft and output drive to a fan shaft to drive the fan at a lower rotational speed than the core shaft. A fan-gearbox axial distance is greater than or equal to 0.35 m. The fan shaft has: (i) a radial bending stiffness ratio of a radial bending stiffness of the fan shaft at the fan input to a radial bending stiffness of the fan shaft at the gearbox output that is greater than or equal to 6.0×10−3; and/or (ii) a tilt stiffness ratio of a tilt stiffness of the fan shaft at the fan input to a tilt stiffness of the fan shaft at the gearbox output that is greater than or equal to 2.5×10−2.
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Patent Agency Ranking
公开(公告)号：US10816087B2
公开(公告)日：2020-10-27
申请号：US16198253
申请日：2018-11-21
Applicant: Rolls-Royce Deutschland Ltd & Co KG , Rolls-Royce plc
Inventor： Michael Nique , Christopher Campbell , Mark Spruce
Abstract: A planetary gearing includes a sun gear; a plurality of planet gears, a ring gear; and a plurality of planet pins, wherein respectively one planet pin is arranged inside a planet gear, and the planet pin and the planet gear form a lubricated journal bearing. The planet pin includes an axial bore and an inner surface that comprises an axially forward end and an axially rearward end. The inner diameter of the axial bore of the planet pin varies between the axially forward end and the axially rearward end of the inner surface and has a maximum at least at one axial end. The planet pins respectively form a crowning at their abutment surface such that their outer diameter decreases from a maximum outer diameter towards at least an axial end of the abutment surface, and has a minimum at the axial end.
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公开(公告)号：US12173661B2
公开(公告)日：2024-12-24
申请号：US18507434
申请日：2023-11-13
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：US11946382B2
公开(公告)日：2024-04-02
申请号：US18219967
申请日：2023-07-10
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
CPC classification number: F01D25/18 , F01D25/166 , F02C3/113 , F02C7/06 , F02C7/36 , F02K3/06 , F16H57/0469 , F16H57/0479 , F05D2220/323 , F05D2220/36 , F05D2260/40311 , F16H2057/085
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：US11852081B2
公开(公告)日：2023-12-26
申请号：US17987338
申请日：2022-11-15
Applicant: ROLLS-ROYCE PLC
Inventor： Mark Spruce
CPC classification number: F02C7/36 , F02C7/06 , F05D2220/36 , F05D2260/40311 , F05D2260/98
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：US11781488B2
公开(公告)日：2023-10-10
申请号：US17223200
申请日：2021-04-06
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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