公开(公告)号：US20230358405A1

公开(公告)日：2023-11-09

申请号：US18168912

申请日：2023-02-14

Applicant: ROLLS-ROYCE plc

Inventor： Jonathan KNAPTON ,  Nicholas M. BROWN

IPC: F23R3/28 ,  F02C7/22

CPC classification number: F23R3/286 ,  F02C7/222

Abstract: A fuel spray nozzle includes a fuel circuit having in series a gallery, circumferentially spaced passages arranged in a row around the nozzle, and an annular spin chamber. Each passage has an inlet for receiving a respective portion of the fuel from the gallery and a metering orifice for discharging its portion of the fuel. The passages are configured such that, when the flow of liquid fuel to the inlet port is shut off, a respective differential static pressure develops across stagnant liquid fuel remaining between the inlet and the metering orifice of each passage, and the passages are further configured such that one or more selected passages develop a different differential static pressure to the remaining passages causing a flow of purging air to enter the gallery from the combustor through the selected passages and exit through the remaining passages, thereby purging the gallery and the passages of fuel.

公开(公告)号：US11811283B2

公开(公告)日：2023-11-07

申请号：US17007338

申请日：2020-08-31

Applicant: ROLLS-ROYCE plc

Inventor： David F. Brookes

IPC: H02K3/28 ,  H02K1/16 ,  H02K3/14 ,  H02K3/24 ,  H02K3/42 ,  H02K3/493 ,  H02K15/00 ,  H02K15/02 ,  H02K15/085 ,  H02K15/12 ,  H02K21/14 ,  H02K7/18 ,  H02K9/197

CPC classification number: H02K3/28 ,  H02K1/165 ,  H02K3/14 ,  H02K3/24 ,  H02K3/42 ,  H02K3/493 ,  H02K7/1823 ,  H02K9/197 ,  H02K15/0018 ,  H02K15/024 ,  H02K15/085 ,  H02K15/12 ,  H02K21/14 ,  H02K2213/06

Abstract: A stator for a radial-flux rotary electric machine includes a yoke with a plurality of teeth, each tooth extending from a root at the yoke to a tip. The stator further includes a plurality of coils, each one of which being located on a respective one of the plurality of teeth, the coils being sized such that a slot fill factor is between zero and unity to define axial voids in the slots. The stator further includes a plurality of magnetic sealing members, each one of which being engaged with the tips of adjacent teeth to circumferentially and axially seal the axial voids in the slots for retaining an axial flow of coolant therein, the magnetic sealing members being composed of a magnetic material to provide a flux path between adjacent tooth tips to increase an amount of leakage flux.

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

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

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.

公开(公告)号：US20230332509A1

公开(公告)日：2023-10-19

申请号：US18208006

申请日：2023-06-09

Applicant: ROLLS-ROYCE plc

Inventor： Caroline L TURNER

IPC: F01D15/10 ,  F02C3/113

CPC classification number: F01D15/10 ,  F02C3/113

Abstract: In a gas turbine engine of the type having a high-pressure (HP) spool and a low-pres sure (LP) spool, methods of increasing surge margin and compression efficiency at a given thrust are provided. One method increases compression efficiency and includes transferring mechanical power from the HP spool to the LP spool to reduce a corrected speed of a HP compressor therein and raise a working line of a LP compressor therein. Another method increases surge margin and includes transferring mechanical power from the LP spool to the HP spool to increase a corrected speed of a HP compressor therein and lower a working line of a LP compressor therein.

公开(公告)号：US11788616B2

公开(公告)日：2023-10-17

申请号：US17814019

申请日：2022-07-21

Applicant: ROLLS-ROYCE plc

Inventor： Fiona Halliday ,  Mark Spruce

IPC: F16H57/08 ,  F16C17/02

CPC classification number: F16H57/08 ,  F16C17/02 ,  F16C2202/22 ,  F16C2360/23 ,  F16C2361/61 ,  F16H2057/085

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.

公开(公告)号：US20230323824A1

公开(公告)日：2023-10-12

申请号：US18098433

申请日：2023-01-18

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN ,  Christopher P MADDEN ,  Craig W BEMMENT

IPC: F02C9/40 ,  F02C9/28

CPC classification number: F02C9/40 ,  F02C9/28 ,  F05D2270/31 ,  F05D2220/323 ,  F05D2270/306 ,  F05D2220/80

Abstract: A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.

公开(公告)号：US11781672B1

公开(公告)日：2023-10-10

申请号：US18058459

申请日：2022-11-23

Applicant: ROLLS-ROYCE plc

Inventor： Christopher A. Murray

IPC: F16K31/126 ,  F16K1/12 ,  F16K17/04 ,  F02C7/28 ,  F02C6/08 ,  F04D27/02

CPC classification number: F16K31/126 ,  F16K1/123 ,  F16K31/1266 ,  F02C6/08 ,  F02C7/28 ,  F04D27/0215 ,  F05D2260/606 ,  F05D2270/65 ,  F16K17/0493

Abstract: A valve assembly includes a fluid flow passage, a valve seat, and an actuator assembly. The actuator assembly includes an actuator body stationary relative to the valve seat and a valve member moveable relative to the valve seat between a first position in which the valve member engages the valve seat, and a second position in which the valve member is remote from the valve seat. The valve member includes at least one orifice extending therethrough. The actuator assembly further includes a bellows attached to the valve member and to the actuator body. An interior surface of the bellows, the actuator body, and the valve member define a control chamber therebetween. An exterior surface of the bellows and the valve member define an outer volume therebetween such that the outer volume is around the control chamber. The at least one orifice fluidly communicates the control chamber with the outer volume.

公开(公告)号：US11773737B1

公开(公告)日：2023-10-03

申请号：US17733135

申请日：2022-04-29

Applicant: Rolls-Royce PLC

Inventor： Michael John Whittle ,  Donka Novovic ,  James William Philip Montgomery

IPC: F01D9/04 ,  F01D11/00

CPC classification number: F01D9/042 ,  F01D11/005 ,  F05D2240/11 ,  F05D2300/20

Abstract: A stator vane assembly for a gas turbine engine is disclosed. The stator vane assembly includes an inner carrier including a metallic material and an outer carrier including a metallic material. The stator vane assembly further includes a ceramic-containing airfoil that extends from the inner carrier to the outer carrier and is at least partially received by the inner carrier and the outer carrier. The stator vane assembly further includes a load transfer device disposed between the airfoil and at least one of the inner carrier and the outer carrier. The load transfer device includes a support member fixedly attached to the at least one of the inner carrier and the outer carrier, and a plurality of micropillars coupled to the support member and extending towards the airfoil. Each micropillar is deformable and engages the airfoil.

公开(公告)号：US11773735B2

公开(公告)日：2023-10-03

申请号：US17560202

申请日：2021-12-22

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Daniel Clark ,  Carl Boettcher ,  David Wright

IPC: F01D9/04 ,  F01D25/00

CPC classification number: F01D9/041 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2300/20

Abstract: A turbine vane assembly for use in a gas turbine engine includes turbine vanes, a segmented inner vane support, and an outer vane support. The turbine vanes are arranged around a central axis of the engine. The inner vane support is arranged radially inwardly of the turbine vanes. The outer vane support includes a full-hoop outer support ring located radially outward of the plurality of turbine vanes and extends entirely circumferentially about the central axis. The outer vane support further includes a plurality of discrete support spars coupled to the full-hoop outer support ring and extending radially inward from the full-hoop outer support ring through an interior cavity of a respective turbine vane.

公开(公告)号：US11761856B2

公开(公告)日：2023-09-19

申请号：US16950260

申请日：2020-11-17

Applicant: ROLLS-ROYCE plc

Inventor： Paul A Flint ,  Adriano Pulisciano ,  Bilal M Nasser

IPC: G01M15/14 ,  G01B11/00 ,  G01N21/95

CPC classification number: G01M15/14 ,  G01B11/005 ,  G01N21/95

Abstract: A method comprising: inspecting an engine during a first period of time to identify damage, the engine being associated with an aircraft; receiving three-dimensional data of one or more components of the engine, the three-dimensional data being generated during the first period of time; determining, during the first period of time, whether the identified damage exceeds a threshold; providing instructions to release the aircraft for operation in a second period of time, subsequent to the first period of time, if the identified damage does not exceed the threshold; and inspecting the received three-dimensional data during the second period of time to measure damage.