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公开(公告)号：US20220186670A1
公开(公告)日：2022-06-16
申请号：US17603218
申请日：2020-04-27
Applicant: Rolls-Royce Deutschland Ltd & Co KG , Rolls-Royce plc
Inventor： Greg BLAKE , Lucia CICIRIELLO , Mark SPRUCE , Matthew WILSON
Abstract: Embodiments of the invention are shown in the figures, where a method for manufacturing a gearbox, the method comprising: providing a predefined interval around an integer; providing a gearbox setup; determining a speed ratio of at least two components of the gearbox setup; comparing the speed ratio with the predefined interval around the integer; and manufacturing a gearbox in accordance with the gearbox setup in dependence on the comparison.
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公开(公告)号：US20210404390A1
公开(公告)日：2021-12-30
申请号：US17244091
申请日：2021-04-29
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
IPC: F02C7/36 , F02K3/06 , F16H57/025 , F16H57/08
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. A moment of inertia of the fan is greater than or equal to 7.40×107 kgm2. 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−3. A tilt stiffness to moment of inertia ratio of: the tilt stiffness of at least one of the fan shaf 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 Nrad−1kg−1m−1.
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公开(公告)号：US20210172378A1
公开(公告)日：2021-06-10
申请号：US16820903
申请日：2020-03-17
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: A gas turbine engine (10) for an aircraft comprising: an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine to the compressor; a fan (23) located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox (30) that receives an input from the core shaft (26) and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, the gearbox (30) being an epicyclic gearbox (30) comprising a sun gear (28), a plurality of planet gears (32), a ring gear (38), and a planet carrier (34) arranged to have the plurality of planet gears (32) mounted thereon; and a gearbox support (40) arranged to at least partially support the gearbox within the engine. The gearbox (30) has a cross sectional area, the cross sectional area being greater than or equal to 2.4×10−1 m2; and a first gearbox support strength ratio of: the torsional strength of the gearbox support ( 40 ) the radial bending stiffness of the gearbox support ( 40 ) × the cross sectional area of the gearbox is greater than or equal to 7.0×10−3. A planet gear spacing angle in radians (β) is defined as 2π/N, where N is the number of planet gears (32). A second gearbox support strength ratio of: the torsional strength of the gearbox support ( 40 ) the tilt stiffness of the gearbox support ( 40 ) × the planet gear spacing angle ( β ) is greater than or equal to 1.0×10−1.
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公开(公告)号：US20190162293A1
公开(公告)日：2019-05-30
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
CPC classification number: F16H57/08 , F01D25/18 , F02C7/36 , F05D2260/40311 , F05D2260/98 , F16C23/045 , F16C2360/23 , F16C2361/61 , F16H1/28 , F16H1/2836 , F16H57/0479 , F16H57/0486 , F16H57/082 , F16H2057/085
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：US20250035050A1
公开(公告)日：2025-01-30
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−1 m−1 mm−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−1 kg−1 mm−2.
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Patent Agency Ranking
公开(公告)号：US20240426252A1
公开(公告)日：2024-12-26
申请号：US18829971
申请日：2024-09-10
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.
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公开(公告)号：US20240200467A1
公开(公告)日：2024-06-20
申请号：US18588409
申请日：2024-02-27
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：US20230349301A1
公开(公告)日：2023-11-02
申请号：US18219967
申请日：2023-07-10
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
CPC classification number: F01D25/18 , F02C7/36 , F16H57/0469 , F16H57/0479 , F02C7/06 , F02K3/06 , F02C3/113 , F01D25/166 , 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：US20230228218A1
公开(公告)日：2023-07-20
申请号：US18125484
申请日：2023-03-23
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 5.0×1018 N2m−2.
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公开(公告)号：US20230044167A1
公开(公告)日：2023-02-09
申请号：US17814019
申请日：2022-07-21
Applicant: ROLLS-ROYCE plc
Inventor： Fiona HALLIDAY , Mark SPRUCE
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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