-
公开(公告)号：US11725591B2
公开(公告)日：2023-08-15
申请号：US17576218
申请日：2022-01-14
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. A fan-gearbox axial distance is defined as the axial distance between the output of the gearbox and the fan axial centreline, the fan-gearbox axial distance being greater than or equal to 0.35 m.
-
公开(公告)号：US11359548B2
公开(公告)日：2022-06-14
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.
-
公开(公告)号：US11313438B2
公开(公告)日：2022-04-26
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.
-
公开(公告)号：US11162431B2
公开(公告)日：2021-11-02
申请号：US17062695
申请日：2020-10-05
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
Abstract: A gas turbine engine for an aircraft including an engine core including a turbine, compressor, and core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; a gearbox that can receive input from the core shaft and can output drive to the fan at a lower rotational speed than the core shaft, an epicyclic gearbox including a sun gear, planet gears, a ring gear, and a planet carrier on which the planet gears are mounted; and a gearbox support. A first gearbox support shear stress ratio: torsional shear stress of the gearbox support at maxiumum take off conditions radial bending stiffness of the gearbox support is less than or equal to 4.9×101 m−1, and/or a second gearbox ratio: torsional shear stress of the gearbox support at maximum take off conditions tilt stiffness of the gearbox support is less than or equal to 4.1×103 rad/m3.
-
Patent Agency Ranking
公开(公告)号：US11149652B1
公开(公告)日：2021-10-19
申请号：US16995901
申请日：2020-08-18
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.
-
公开(公告)号：US11085523B2
公开(公告)日：2021-08-10
申请号：US16198172
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
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, each planet gear having an axially forward face side and an axially rearward face side; a ring gear engaging the planet gears; and planet slide bearing pins, wherein respectively one planet slide bearing pin is arranged inside a planet gear forming 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, and the planet slide bearing pins respectively form one crowning at their abutment surface such that their outer diameter decreases from a maximum outer diameter to at least an axial end of the abutment surface and has a minimum at the axial end.
-
公开(公告)号：US10859001B1
公开(公告)日：2020-12-08
申请号：US16821496
申请日：2020-03-17
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 output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft; and a gearbox support arranged to at least partially support the gearbox within the engine. A flight cycle ratio of: the torsional shear stress of the gearbox support at maximum takeoff conditions the torsional shear stress of the gearbox support at cruise conditions is less than or equal to 3.20. A method of operating the gas turbine engine is also disclosed.
-
公开(公告)号：US10823084B1
公开(公告)日：2020-11-03
申请号：US16807526
申请日：2020-03-03
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
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; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft 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; and a gearbox support arranged to mount the gearbox within the engine. The fan shaft, core shaft, gearbox and the gearbox support together may form a transmission.
-
公开(公告)号：US10815901B1
公开(公告)日：2020-10-27
申请号：US16807362
申请日：2020-03-03
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.
-
-
-
-
-
-
-
-
Search Results
49
records
(took 0.023 seconds)
