公开(公告)号：US20250092823A1

公开(公告)日：2025-03-20

申请号：US18969412

申请日：2024-12-05

Applicant: ROLLS-ROYCE PLC

Inventor： Natalie C. WONG ,  Thomas S. BINNINGTON ,  David A. JONES ,  Daniel BLACKER

IPC: F02C7/04 ,  B64D27/10 ,  B64D27/20 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D33/10 ,  F01D9/06 ,  F02C7/08 ,  F02C7/12 ,  F02C7/14 ,  F02C7/18 ,  F02K3/06 ,  F02K3/075 ,  F02K3/115

Abstract: An aircraft comprises a machine body which encloses a turbofan gas turbine engine. The turbofan gas turbine engine includes a heat exchanger module, fan assembly, compressor module, turbine module, and exhaust module. The heat exchanger module communicates with the fan assembly by an inlet duct. The heat exchanger module includes first heat transfer elements that transfer heat energy from a first fluid within the transfer elements to an airflow passing over a surface of the transfer elements before entry of the airflow into a fan assembly inlet. The first fluid contained within transfer elements has a temperature, and the airflow passing over the transfer element surface has a temperature. The turbofan gas turbine engine further includes at least one second heat transfer element, with the or each second heat transfer element transfers heat energy from the first fluid to a second fluid.

公开(公告)号：US12253000B2

公开(公告)日：2025-03-18

申请号：US17795072

申请日：2021-01-18

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

Inventor： David Williams ,  Stefan Menczykalski ,  Stephan Uhkötter ,  Uwe Kracht ,  Wolfram Kurz-Hardjosoekatmo

IPC: F01D25/20 ,  F01M1/20 ,  F02C7/06 ,  F02C7/32 ,  F02C7/36 ,  F15B1/26 ,  F16H57/04

Abstract: An oil system of a gas turbine engine, includes a first oil circuit and a second oil circuit. Via the oil circuits, oil is supplied to a hydraulic load of a transmission of the engine. Downstream of the load, in the region of a return of the transmission, oil is introduced into the oil circuits from the transmission. Upstream of the load, in the region of inlets, oil can be introduced into the transmission from the oil circuits. The second oil circuit includes an oil accumulator between the return and the inlet of the second oil circuit. The oil accumulator is configured such that, according to a feed pressure of the oil upstream of the inlet, oil is stored in the oil accumulator or oil stored in the oil accumulator is fed toward the inlet.

公开(公告)号：US12252996B2

公开(公告)日：2025-03-18

申请号：US18625842

申请日：2024-04-03

Applicant: ROLLS-ROYCE plc

Inventor： Andrew Parsley ,  Natalie C Wong

IPC: F01D21/14

Abstract: An apparatus and method for reducing a pressure differential across a turbine 19 of a gas turbine engine 10 during a shaft break event, comprises a pressure equalization apparatus 300, 400, 500, 600, 700 configured to introduce a pressurised fluid into a core airflow A at a region downstream of the turbine 19, wherein a rearward movement of the turbine 19 or a shaft 26 in a shaft break event directly actuates the pressure equalisation apparatus 300, 400, 500, 600, 700 to directly increase a local pressure at the downstream region 29 of the turbine 19 and thereby reduce the pressure differential across the turbine 19. The reduction in the pressure differential may result in a reduction in the acceleration of the turbine 19.

公开(公告)号：US20250084768A1

公开(公告)日：2025-03-13

申请号：US18808248

申请日：2024-08-19

Applicant: ROLLS-ROYCE plc

Inventor： Andrew MEKERESZ ,  Anastasios KOVANIS ,  John J. BOLGER ,  Benedict R PHELPS

IPC: F01D11/00

Abstract: An annulus filler of a gas turbine engine includes an outer lid including a leading edge, a trailing edge, a first longitudinal edge, a second longitudinal edge, and an outer radial surface. The outer radial surface includes a first nominal surface portion and a second nominal surface portion. The outer radial surface further includes a protruding surface portion extending radially outwardly from each of the first nominal surface portion and the second nominal surface portion and a recessed surface portion extending radially inwardly from each of the first nominal surface portion and the second nominal surface portion. Each of the protruding surface portion and the recessed surface portion is configured to redirect an air drawn through the gas turbine engine.

公开(公告)号：US20250075639A1

公开(公告)日：2025-03-06

申请号：US18794116

申请日：2024-08-05

Applicant: ROLLS-ROYCE plc

Inventor： Jack F. COLEBROOKE

IPC: F01D25/28

Abstract: A ducting arrangement for a gas turbine engine and a method of assembling such a ducting arrangement, wherein in the gas turbine engine includes an outer annular duct structure with an outer mount and an inner annular duct structure with an inner mount. The inner annular duct structure is configured to be received within the outer annular duct structure such that the inner mount and the outer mount are angularly aligned. In one aspect, the inner mount and the outer mount are coupled together by a tension tie to attach the outer annular duct structure to the inner annular duct structure, the tension tie being a cable or a wire. In another aspect, the inner mount and the outer mount are configured to be coupled together by a tension tie formed by a cable or a wire to attach the outer annular duct structure to the inner annular duct structure.

公开(公告)号：US12240983B2

公开(公告)日：2025-03-04

申请号：US18062041

申请日：2022-12-06

Applicant: ROLLS-ROYCE plc

Inventor： John R. Nicholls ,  Victoria Louise Minns ,  David S. Rickerby

IPC: C23C2/12 ,  C09D1/00 ,  C23C22/20 ,  C23C22/78

Abstract: A method of forming a protective coating. The method includes providing a substrate including at least one chemical element and a surface; forming a basecoat composition including an aluminium phase including aluminium; applying the basecoat composition on the surface of the substrate to form a basecoat layer; heating the basecoat layer to a first temperature for a predetermined period of time; applying a glow discharge plasma on the basecoat layer; and heating the basecoat layer to a second temperature greater than the first temperature, in order to activate an exothermic reaction between at least the aluminium phase of the basecoat layer and the at least one chemical element of the substrate, wherein the exothermic reaction forms the protective coating on the surface of the substrate.

公开(公告)号：US12240614B2

公开(公告)日：2025-03-04

申请号：US18209136

申请日：2023-06-13

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden

IPC: B64D37/04 ,  B64D27/10 ,  B64D41/00 ,  F02C7/22 ,  F02C9/26

Abstract: A power system for an aircraft includes one or more gas turbine engines arranged to burn a fuel so as to provide power to the aircraft; a plurality of fuel tanks each arranged to contain a fuel to be used to provide power to the aircraft; and a fuel manager. At least two of the fuel tanks contain different fuels, which have different proportions of a sustainable aviation fuel. The fuel manager is arranged to store information on the fuel contained in each fuel tank; and to control fuel supply so as to select a specific fuel accordingly to power at least the majority of operations on the ground. The fuel manager may additionally identify which tank contains the fuel with the highest proportion of a sustainable aviation fuel; and that fuel may be used to power at least the majority of operations on the ground.

公开(公告)号：US20250067434A1

公开(公告)日：2025-02-27

申请号：US18804670

申请日：2024-08-14

Applicant: ROLLS-ROYCE PLC

Inventor： Marcin Damian DUTKA

IPC: F23R3/00 ,  F02C7/12

Abstract: A tile for a gas turbine engine combustor. The tile has a base that has a hot-side surface, a cold-side surface, a first circumferential extremity, a second circumferential extremity and a local radial axis. The tile also has a plurality of cooling channels that have inlets on the cold-side surface and outlets on the hot-side surface, and one or more rail structure attached to the cold-side surface of the base.

公开(公告)号：US12234019B2

公开(公告)日：2025-02-25

申请号：US18045857

申请日：2022-10-12

Applicant: ROLLS-ROYCE plc

Inventor： Christopher A Murray

IPC: B64D13/06 ,  F02C7/32 ,  F02C7/36

Abstract: A cabin blower system, for an aircraft, comprising: a cabin blower compressor, for compressing air for delivery to a cabin of an aircraft, comprising a compressor drive shaft running on a contactless bearing system; and a transmission comprising an input and an output, the input being arranged to receive power from an engine of the aircraft and the output being arranged to mechanically drive the cabin blower compressor, wherein the output of the transmission is mechanically coupled with the compressor drive shaft via a flexible drive coupling.

公开(公告)号：US12228077B2

公开(公告)日：2025-02-18

申请号：US18183989

申请日：2023-03-15

Applicant: ROLLS-ROYCE plc

Inventor： Jonathan E. Holt ,  Richard Sharpe

IPC: F02C7/224 ,  B64D13/02 ,  B64D37/30 ,  F02C7/32

Abstract: Disclosed is a fuel system for a gas turbine engine. The system comprises a fuel pump for fluid communication with a fuel reservoir; a driving turbine for driving the fuel pump; and a source of compressed air flow to drive the driving turbine. The source of compressed air may be the engine core, a dedicated fuel system compressor or the compressor of a cabin blower system.