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公开(公告)号：US20250067220A1
公开(公告)日：2025-02-27
申请号：US18947605
申请日：2024-11-14
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：US20230092426A1
公开(公告)日：2023-03-23
申请号：US17966318
申请日：2022-10-14
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：US20230054031A1
公开(公告)日：2023-02-23
申请号：US17881225
申请日：2022-08-04
Applicant: ROLLS-ROYCE plc
Inventor： Fiona HALLIDAY , Mark SPRUCE
Abstract: A shaft component, which in particular can be connected or is connected to the input or output side of a gear box in a gas turbine engine, in particular an aircraft engine, wherein the shaft component has at least two regions comprising fiber reinforced plastic, with fibers in the at least two regions differing in their composition, their geometric properties, their density, their radial position, their axial position and/or in their fiber orientation in the shaft component.
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公开(公告)号：US20210404391A1
公开(公告)日：2021-12-30
申请号：US17473181
申请日：2021-09-13
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: The present disclosure relates to 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 comprising: 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：US20210262395A1
公开(公告)日：2021-08-26
申请号：US17106783
申请日：2020-11-30
Applicant: ROLLS-ROYCE PLC
Inventor： Mark SPRUCE
Abstract: A gas turbine engine for an aircraft includes an engine core with a turbine, a compressor, and a core shaft connecting the turbine and compressor; a fan upstream of the engine core including a plurality of fan blades; and a gearbox that receives an input from a gearbox input shaft portion of the core shaft and outputs drive to a fan shaft so as to drive the fan at a lower rotational speed than the core shaft, the gearbox being an epicyclic gearbox including a sun gear, a plurality of planet gears, a ring gear, and a planet carrier arranged to have the plurality of planet gears mounted thereon, and wherein the sun gear receives input from the core shaft. At cruise conditions the torque on the core shaft is greater than 10,000 Nm and a ratio of core shaft stiffness to core shaft torque is within a specified range.
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Patent Agency Ranking
公开(公告)号：US20210222631A1
公开(公告)日：2021-07-22
申请号：US17062695
申请日：2020-10-05
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: A gas turbine engine for an aircraft including an engine core including a turbine, compressor, and core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; a gearbox that can receive input from the core shaft and can output drive to the fan at a lower rotational speed than the core shaft, an epicyclic gearbox including a sun gear, planet gears, a ring gear, and a planet carrier on which the planet gears are mounted; and a gearbox support. A first gearbox support shear stress ratio: torsional shear stress of the gearbox support at maxiumum take off conditions radial bending stiffness of the gearbox support is less than or equal to 4.9×101 m−1, and/or a second gearbox ratio: torsional shear stress of the gearbox support at maximum take off conditions tilt stiffness of the gearbox support is less than or equal to 4.1×103 rad/m3.
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公开(公告)号：US20250035051A1
公开(公告)日：2025-01-30
申请号：US18913194
申请日：2024-10-11
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: A gas turbine engine configured with an engine core. A fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a gearbox arranged to receive an input from 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 being an epicyclic gearbox comprising a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted, the planet carrier having an effective linear torsional stiffness and the gearbox having a gear mesh stiffness between the planet gears and the ring gear. Additionally, the product of the effective linear torsional stiffness of the planet carrier and the gear mesh stiffness between the planet gears and the ring gear is greater than or equal to 5.0×1018 N2m−2.
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公开(公告)号：US20230296056A1
公开(公告)日：2023-09-21
申请号：US18131493
申请日：2023-04-06
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
CPC classification number: F02C7/36 , F02K3/06 , F05D2200/14 , F05D2220/323 , F05D2220/36 , F05D2260/40311
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.
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公开(公告)号：US20230075036A1
公开(公告)日：2023-03-09
申请号：US17987338
申请日：2022-11-15
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：US20210262396A1
公开(公告)日：2021-08-26
申请号：US17119379
申请日：2020-12-11
Applicant: ROLLS-ROYCE PLC
Inventor： Mark SPRUCE
Abstract: An engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising 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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