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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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公开(公告)号：US11525408B2
公开(公告)日：2022-12-13
申请号：US17378243
申请日：2021-07-16
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：US11408354B2
公开(公告)日：2022-08-09
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：US10982563B1
公开(公告)日：2021-04-20
申请号：US16990302
申请日：2020-08-11
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：US10961918B1
公开(公告)日：2021-03-30
申请号：US16807744
申请日：2020-03-03
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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Patent Agency Ranking
公开(公告)号：US10914241B1
公开(公告)日：2021-02-09
申请号：US17029539
申请日：2020-09-23
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 comprising a plurality of fan blades; and a gearbox. The gearbox receives an input from a gearbox input shaft portion of the core shaft and outputs 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 including a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The carrier and the gearbox input shaft each have a torsional stiffness, and a carrier to gearbox input shaft torsional stiffness ratio is greater than or equal to 70.
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公开(公告)号：US20210017911A1
公开(公告)日：2021-01-21
申请号：US16515733
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 rate. The output shaft is coupled to the fan to drive the fan at the reduced rate and provide trust for the gas turbine engine.
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公开(公告)号：US20210017910A1
公开(公告)日：2021-01-21
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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公开(公告)号：US12297779B2
公开(公告)日：2025-05-13
申请号：US18433932
申请日：2024-02-06
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
Abstract: Gas turbine engine for aircraft includes: an engine core including a turbine, compressor, and core shaft connecting the turbine to the compressor; a fan located upstream of the core; a gearbox; and a gearbox support arranged to at least partially support the gearbox. The fan has a mass in a range of 150 kg to 1200 kg. A moment of inertia of the fan is greater than or equal to 7.40×107 kgmm2. A radial bending stiffness to moment of inertia ratio of: the radial bending stiffness of at least one of the fan shaft at the output of the gearbox and the gearbox support the moment of inertia of the fan may be greater than or equal to 2.5×10−2 Nkg−1m−1mm−2. A tilt stiffness to moment of inertia ratio of: the tilt stiffness of at least one of the fan shaft at the output of the gearbox and the gearbox support the moment of inertia of the fan may be greater than or equal to 4.0×10−4 Nmrad−1kg−1mm−2.
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公开(公告)号：US12116938B2
公开(公告)日：2024-10-15
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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