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公开(公告)号：US11840965B2
公开(公告)日：2023-12-12
申请号：US17980230
申请日：2022-11-03
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
CPC classification number: F02C7/36 , F16H1/28 , F16H2057/02039
Abstract: A gas turbine engine for an aircraft configured with an engine core that has a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, that has a plurality of fan blades. A gearbox arranged to receive an input from the core shaft and to output to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The gearbox having an overall gear mesh stiffness, and wherein the overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m and less than or equal to 8.0×109 N/m.
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公开(公告)号：US11788616B2
公开(公告)日：2023-10-17
申请号：US17814019
申请日：2022-07-21
Applicant: ROLLS-ROYCE plc
Inventor： Fiona Halliday , Mark Spruce
CPC classification number: F16H57/08 , F16C17/02 , F16C2202/22 , F16C2360/23 , F16C2361/61 , F16H2057/085
Abstract: A journal bearing comprising a first component and a second component, the first and second components being arranged to rotate relative to one another in normal use. The first component comprises a first body, a first layer forming a functional surface facing the second component, and a first subsurface layer between the body and the layer. The first subsurface layer is formed of a material having a first coefficient of thermal expansion in the radial direction, and the first body is formed of a material having a second coefficient of thermal expansion in the radial direction. The first coefficient of thermal expansion is lower than the second coefficient of thermal expansion.
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公开(公告)号：US11542873B2
公开(公告)日：2023-01-03
申请号：US17827214
申请日：2022-05-27
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：US11421552B2
公开(公告)日：2022-08-23
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：US11274729B2
公开(公告)日：2022-03-15
申请号：US16515730
申请日：2019-07-18
Applicant: Rolls-Royce plc
Inventor： Mark Spruce
Abstract: A gas turbine engine includes an engine core, a fan and a gearbox interconnecting the engine core and the fan. The engine core is configured to drive rotation of at least one shaft. The power gearbox is configured to transfer torque from the at least one shaft to an output shaft at a reduced rotational speed. The output shaft is coupled to the fan to drive the fan at the reduced speed and provide trust for the gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US11098656B2
公开(公告)日：2021-08-24
申请号：US17062272
申请日：2020-10-02
Applicant: ROLLS-ROYCE PLC
Inventor： Mark Spruce
Abstract: A gas turbine engine for an aircraft has an engine core having a turbine, compressor, and core shaft connecting the turbine and compressor; a fan upstream the engine core, the fan having fan blades; and a gearbox. The gearbox receives an input from a core shaft and outputs drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, planet gears, ring gear, and planet carrier on which the planet gears are mounted. The gearbox has a gear mesh stiffness between the planet gears and the ring gear and a gear mesh stiffness between the planet gears and the sun gear. The gear mesh stiffness between the planet gears and the ring gear divided by that between the planet gears and the sun gear is in the range from 0.90 to 1.28.
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公开(公告)号：US10808626B1
公开(公告)日：2020-10-20
申请号：US16807956
申请日：2020-03-03
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
Abstract: An engine for an aircraft includes 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; and a gearbox. The gearbox is arranged to receive an input from a core shaft and to output drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and includes a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. A ratio of radial bending stiffness of the planet carrier to torsional stiffness of the planet carrier is within a specified range.
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公开(公告)号：US12215632B2
公开(公告)日：2025-02-04
申请号：US18384640
申请日：2023-10-27
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
Abstract: A gas turbine engine for an aircraft configured with an engine core that has a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, that has a plurality of fan blades. A gearbox arranged to receive an input from the core shaft and to output to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The gearbox having an overall gear mesh stiffness, and wherein the overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m and less than or equal to 8.0×109 N/m.
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公开(公告)号：US11643974B2
公开(公告)日：2023-05-09
申请号：US17544660
申请日：2021-12-07
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
CPC classification number: F02C7/36 , F16H1/28 , F16H57/082 , F05D2220/323
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 5.0×1018N2m−2.
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公开(公告)号：US11378015B2
公开(公告)日：2022-07-05
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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