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公开(公告)号：US20220364481A1
公开(公告)日：2022-11-17
申请号：US17863836
申请日：2022-07-13
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：US20220298975A1
公开(公告)日：2022-09-22
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：US20220090541A1
公开(公告)日：2022-03-24
申请号：US17544660
申请日：2021-12-07
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: An engine core including a turbine, compressor, and a core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from the core shaft and to output drive to the 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, ring gear, and planet carrier to the mounted planet gears. The planet carrier has an effective linear torsional stiffness and the gearbox has a gear mesh stiffness between the planet gears and the ring gear. A carrier to ring mesh ratio of: the effective linear torsional stiffness of the planet carrier gear mesh stiffness between the planet gears and the ring gear is greater than or equal to 0.2.
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公开(公告)号：US20220056852A1
公开(公告)日：2022-02-24
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：US20210310420A1
公开(公告)日：2021-10-07
申请号：US17223200
申请日：2021-04-06
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, 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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Patent Agency Ranking
公开(公告)号：US20210310418A1
公开(公告)日：2021-10-07
申请号：US17197279
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：US20210172379A1
公开(公告)日：2021-06-10
申请号：US16820963
申请日：2020-03-17
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: An engine core including a turbine, compressor, and a core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from the core shaft and to output drive to the 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, ring gear, and planet carrier to the mounted planet gears. The planet carrier has an effective linear torsional stiffness and the gearbox has a gear mesh stiffness between the planet gears and the ring gear. A carrier to ring mesh ratio of: the effective linear torsional stiffness of the planet carrier gear mesh stiffness between the planet gears and the ring gear is greater than or equal to 0.2.
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公开(公告)号：US20240295193A1
公开(公告)日：2024-09-05
申请号：US18640748
申请日：2024-04-19
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：US20240191660A1
公开(公告)日：2024-06-13
申请号：US18237580
申请日：2023-08-24
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
IPC: F02C7/36 , B64D27/10 , B64D35/02 , F01D5/02 , F01D15/12 , F16C1/02 , F16C1/08 , F16C3/02 , F16H1/28 , F16H1/32 , F16H57/02
CPC classification number: F02C7/36 , B64D27/10 , B64D35/02 , F01D5/026 , F01D15/12 , F16C1/02 , F16C1/08 , F16C3/02 , F16H1/32 , F16H57/02 , F05D2220/323 , F05D2260/40311 , F16C2202/06 , F16C2326/43 , F16C2360/23 , F16C2361/65 , F16H1/28 , F16H2001/327 , F16H2057/02039
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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公开(公告)号：US20240011442A1
公开(公告)日：2024-01-11
申请号：US18130225
申请日：2023-04-03
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
CPC classification number: F02C7/36 , F16H57/082 , F05D2260/40311 , F05D2300/501 , F05D2200/14 , 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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