公开(公告)号：US20210172508A1

公开(公告)日：2021-06-10

申请号：US16821094

申请日：2020-03-17

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F16H55/08 ,  F02C7/36 ,  F16H55/14 ,  F16H55/06

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 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, a ring gear, and a planet carrier on which the planet gears are mounted, the gearbox having an overall gear mesh stiffness. The overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m. The gearbox has a gearbox diameter defined as the pitch circle diameter of the ring gear. Optionally, the gearbox diameter is in the range from 0.55 m to 1.2 m.

公开(公告)号：US20210172383A1

公开(公告)日：2021-06-10

申请号：US17161004

申请日：2021-01-28

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F16H1/28

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.

公开(公告)号：US20210172380A1

公开(公告)日：2021-06-10

申请号：US17062272

申请日：2020-10-02

Applicant: ROLLS-ROYCE PLC

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F16H1/28

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.

公开(公告)号：US20190162294A1

公开(公告)日：2019-05-30

申请号：US16198327

申请日：2018-11-21

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Michael NIQUE ,  Paul GORENZ ,  Christopher CAMPBELL ,  Frank WAGNER ,  Mark SPRUCE ,  Daren ASHMORE

IPC: F16H57/08 ,  F16H1/28 ,  F16H57/04 ,  F02C7/36 ,  F01D25/18

CPC classification number: F16H57/08 ,  F01D25/18 ,  F02C7/36 ,  F05D2260/40311 ,  F05D2260/98 ,  F16C17/02 ,  F16C23/045 ,  F16C33/1025 ,  F16C2360/24 ,  F16C2361/61 ,  F16H1/28 ,  F16H1/2836 ,  F16H57/0479 ,  F16H2057/085

Abstract: A planetary gearing includes a sun gear rotating about a rotation axis and driven by a sun shaft; planet gears driven by the sun gear; a ring gear engaging the planet gears; and a plurality of planet pins that respectively include an outer-side abutment surface having an axially forward end and an axially rearward end. Respectively, one planet pin is arranged inside a planet gear, and the planet pin and the planet gear form a lubricated journal bearing. At an axially forward face side and/or axially rearward face side, each planet gear forms a recess that extends inside the planet gear starting from the face side. 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 one axial end of the abutment surface, and has a minimum at the axial end.

公开(公告)号：US20250129751A1

公开(公告)日：2025-04-24

申请号：US18990503

申请日：2024-12-20

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F16H1/28 ,  F16H57/02

Abstract: A gas turbine engine for an aircraft comprising 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 having a fan diameter 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, thereby defining a gear ratio. The gearbox being an epicyclic gearbox. A gearbox diameter is defined as the pitch circle diameter of the ring gear; and a geared-fan value defined by a product of the fan diameter and gear ratio, which are divided by the gearbox diameter, being greater than 12.

公开(公告)号：US20250092799A1

公开(公告)日：2025-03-20

申请号：US18814893

申请日：2024-08-26

Applicant: ROLLS-ROYCE plc

Inventor： Russell ADKINS ,  Mark SPRUCE ,  Christopher D. JONES ,  Stephen C. DREW

IPC: F01D25/00

Abstract: A shaft for a gas turbine engine includes a composite tube including a plurality of grooves extending along a longitudinal axis of the shaft. The shaft has a load fuse mechanism that has at least one metallic coupling that has a plurality of splines extending along the longitudinal axis of the shaft. Each of the plurality of splines is received within and engages with a corresponding groove of the composite tube to form a preloaded interference fit between the load fuse mechanism and the composite tube. The at least one metallic coupling includes a first portion defining a first diameter and a second portion extending from the first portion along the longitudinal axis. The second portion defines a second diameter that is greater than the first diameter. The second portion has a smooth annular outer surface devoid of any splines.

公开(公告)号：US20240263587A1

公开(公告)日：2024-08-08

申请号：US18384640

申请日：2023-10-27

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F16H1/28 ,  F16H57/02

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.

公开(公告)号：US20240077035A1

公开(公告)日：2024-03-07

申请号：US18507434

申请日：2023-11-13

Applicant: ROLLS-ROYCE PLC

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F02C7/06

CPC classification number: F02C7/36 ,  F02C7/06 ,  F05D2220/36 ,  F05D2260/40311 ,  F05D2260/98

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.

公开(公告)号：US20230212986A1

公开(公告)日：2023-07-06

申请号：US17980230

申请日：2022-11-03

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F16H1/28 ,  F16H57/02

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.

公开(公告)号：US20220298976A1

公开(公告)日：2022-09-22

申请号：US17836414

申请日：2022-06-09

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  B64D27/12 ,  F02K3/06 ,  F16H1/28

Abstract: A gas turbine engine including: an engine core including a turbine, a compressor, and a core shaft; a fan located upstream of the engine core; a gearbox; and a fan shaft mounting structure including at least two supporting bearings connected to fan shaft. The supporting bearings are located at positions forward of the gearbox. A first bearing separation distance (d1) is defined as an axial distance between the input to the fan and the closest supporting bearing in a rearward direction from the fan. A bearing axial separation (d3) is defined as an axial distance between the closest supporting bearing in the rearward direction from the fan and the closest supporting bearing in a forward direction from the gearbox. A bearing separation ratio defined as: the ⁢ first ⁢ bearing ⁢ separation ⁢ distance ⁢ ( d 1 ) the ⁢ bearing ⁢ axial ⁢ separation ⁢ ( d 3 ) is in a range from 4.1×10−1 to 8.3×10−1.