公开(公告)号：US11434832B2

公开(公告)日：2022-09-06

申请号：US17411617

申请日：2021-08-25

Applicant: ROLLS-ROYCE plc

Inventor： Craig W Bemment

IPC: F02C9/24 ,  F02C9/18 ,  F01D19/00 ,  F02C7/36 ,  F02C7/268

Abstract: A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.

公开(公告)号：US20220275763A1

公开(公告)日：2022-09-01

申请号：US17742620

申请日：2022-05-12

Applicant: ROLLS-ROYCE plc ,  ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Inventor： Jorge CALDERON ,  David BROWN

IPC: F02C9/46 ,  F01D25/16 ,  F02C9/26

Abstract: A gas turbine engine for an aircraft. The engine including: an engine core with a turbine, a compressor, a fan located upstream of the compressor and including a plurality of fan blades, and a core shaft connecting the turbine to the compressor; a gearbox which receives an input from the core shaft and outputs drive, via a driveshaft, to the fan so as to drive the fan at a lower rotational speed than the turbine, the drive shaft and core shaft forming a shaft system.

公开(公告)号：US11428169B2

公开(公告)日：2022-08-30

申请号：US17096175

申请日：2020-11-12

Applicant: ROLLS-ROYCE plc ,  Rolls-Royce Corporation

Inventor： Simon J. Donovan ,  Peter E. Daum ,  Siddharth Ravichandran

IPC: F02C7/28 ,  F01D11/12 ,  F16J15/16

Abstract: An abradable sealing element comprises a substrate and a sealing structure. The sealing structure comprises one or more wall structures extending from the substrate and defining at least one open cell which is filled with abradable material. The one or more wall structures are formed by additive-layer, powder-fed, laser-weld deposition onto the substrate. The one or more wall structures are formed from nickel-based superalloy and constitute from about 10% to about 50% of the total volume of the sealing structure.

公开(公告)号：US20220268216A1

公开(公告)日：2022-08-25

申请号：US17731673

申请日：2022-04-28

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M TOWNES ,  Michael J WHITTLE ,  Pascal DUNNING

IPC: F02C7/36 ,  F01D5/28

Abstract: A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US11421552B2

公开(公告)日：2022-08-23

申请号：US17205870

申请日：2021-03-18

Applicant: ROLLS-ROYCE plc

Inventor： Mark Spruce

IPC: F02C7/36 ,  F01D25/18 ,  F16H57/04 ,  F02C7/06 ,  F02K3/06 ,  F02C3/113 ,  F01D25/16 ,  F16H57/08

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：US11415014B2

公开(公告)日：2022-08-16

申请号：US17170339

申请日：2021-02-08

Applicant: Rolls-Royce plc ,  Rolls-Royce Corporation

Inventor： Michael J. Whittle ,  Daniel K. Vetters ,  Jeffrey A. Walston ,  Eric Koenig

IPC: F01D9/04 ,  F01D5/28

Abstract: The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.

公开(公告)号：US11414198B2

公开(公告)日：2022-08-16

申请号：US16546362

申请日：2019-08-21

Applicant: ROLLS-ROYCE plc

Inventor： Giles E. Harvey

IPC: H02K9/19 ,  H02K7/14 ,  B64D27/24 ,  B64C29/00

Abstract: An aircraft propulsion system comprises a vertical lift propulsor mounted within a wing of the aircraft. The vertical propulsor comprises an electric motor comprising a rotor mounted to a plurality of propulsor blades, the motor further comprising a stator. The rotor is provided radially outwardly of the stator.

公开(公告)号：US11408428B2

公开(公告)日：2022-08-09

申请号：US17174967

申请日：2021-02-12

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Stretton ,  Michael C Willmot

IPC: F04D19/00 ,  F01D5/12

Abstract: A gas turbine engine for an aircraft includes an engine core including a turbine, compressor, and core shaft connecting turbine to compressor; a fan located upstream of the engine core and including a plurality of fan blades each having a leading and trailing edge. The turbine includes a lowest pressure turbine stage having a row of rotor blades, each rotor blades extending radially and having a leading and trailing edge. The engine has a fan tip axis that joins a radially outer tip of the leading edge of a fan blade and the radially outer tip of the trailing edge of a rotor blade of the lowest pressure stage. The fan tip axis lies in a longitudinal plane which contains a centreline of engine. A fan axis angle is defined as the angle between fan tip axis and centreline, and is in a range between 10 and 20 degrees.

公开(公告)号：US11408345B2

公开(公告)日：2022-08-09

申请号：US16555212

申请日：2019-08-29

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

Inventor： Isabelle Erickson ,  Adam L. Kempers ,  David Edwards ,  John Gebhard ,  Jeremy Gallagher

IPC: F02C7/14 ,  F01D25/20 ,  F02C7/32 ,  F02C7/36 ,  F16H57/04 ,  F16H57/08

Abstract: An oil delivery system is provided that includes a tank for a gas turbine engine, where the tank is positioned radially outward from a compressor section, a combustor section, and/or a turbine section of the gas turbine engine. The tank is configured to store oil for the gas turbine engine. The oil delivery system further includes a primary lubrication system including a sump of a power gearbox, a pump, and an oil feed line. The oil feed line extends from the tank to the primary lubrication system. The oil feed line is configured to allow a flow of oil to pass from the tank to the pump and from the pump through the power gearbox to the sump of the power gearbox.

公开(公告)号：US11407517B2

公开(公告)日：2022-08-09

申请号：US16394280

申请日：2019-04-25

Applicant: ROLLS-ROYCE plc

Inventor： David P Scothern

IPC: B64D27/12 ,  B64D27/24 ,  F01D15/10 ,  F02C6/20 ,  B64D27/02

Abstract: A hybrid aircraft propulsion system. The system comprises a gas turbine engine comprising a compressor, a combustor, one or more turbines, a shaft coupled to one of the turbines, and a bypass fan mechanically driven by the shaft. The system further comprises an electrical generator mechanically coupled to the shaft, and an auxiliary propulsor mechanically coupled to an electric motor and electrically coupled to the electric generator. At maximum power, the gas turbine engine is configured to produce a turbine entry temperature at maximum power between 1800 Kelvin and 2000 Kelvin, the engine comprises a fan bypass ratio of between 4:1 and 13:1, and the generator is configured to absorb between 10% and 60% of the mechanical power generated by the turbine.