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.

公开(公告)号：US11761448B2

公开(公告)日：2023-09-19

申请号：US16395996

申请日：2019-04-26

Applicant: ROLLS-ROYCE plc

Inventor： Giles E Harvey

IPC: F04D25/06 ,  B64D27/24 ,  B64D35/02

CPC classification number: F04D25/06 ,  B64D27/24 ,  B64D35/02

Abstract: The present disclosure concerns an electric aircraft propulsion system. Example embodiments include an aircraft propulsion system (200) comprising: a fan (213) mounted on a central shaft (214); a first electric motor (215) mounted on the central shaft (214) and arranged to drive rotation of the fan (213) via the central shaft; and a second electric motor (216) arranged to drive rotation of the fan (213) via the central shaft (214), wherein the second electric motor (216) is coaxially mounted downstream of the first electric motor (215) and an outer diameter (D2) of the second electric motor (216) is smaller than an outer diameter (D1) of the first electric motor (215).

公开(公告)号：US11761380B2

公开(公告)日：2023-09-19

申请号：US17484873

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C Wong ,  Thomas S Binnington ,  David A Jones ,  Daniel Blacker

IPC: F02C7/14

CPC classification number: F02C7/14 ,  F05D2260/213 ,  F05D2270/20

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter PEX (W/N) defined as PEX=H/T is 0.4 to 6.0.

公开(公告)号：US20230286658A1

公开(公告)日：2023-09-14

申请号：US18170604

申请日：2023-02-17

Applicant: ROLLS-ROYCE plc

Inventor： Graeme E F SUTCLIFFE ,  Richard G MOCHRIE ,  Jade WHITTLE

IPC: F02K7/16 ,  F02C7/04

CPC classification number: F02K7/16 ,  F02C7/04 ,  F05D2220/10 ,  F05D2220/323 ,  F05D2240/10 ,  F05D2260/213

Abstract: A ram-air duct system includes a ram-air duct configured to receive a flow of ram-air from a ram-air inlet and discharge the flow to a ram-air outlet. The system also includes a heat exchanger configured to exchange heat with air within the ram-air duct, an auxiliary air passageway and an electrically-driven air mover configured to move a flow of auxiliary air along the auxiliary air passageway for discharge into the ram-air duct through an intermediate inlet between the ram-air inlet and the ram-air outlet. The air duct system further includes a controller configured to selectively operate the ram-air duct system in an auxiliary supply mode in which the air mover and/or a control valve are controlled to cause the flow of auxiliary air to be discharged into the duct through the intermediate inlet, to thereby control a rate of heat exchange between the heat exchanger and air within the duct.