公开(公告)号：US20240399445A1

公开(公告)日：2024-12-05

申请号：US18667726

申请日：2024-05-17

Applicant: ROLLS-ROYCE PLC

Inventor： Neil D'SOUZA ,  Kevin GOODWIN ,  John D LEHANE ,  Martin R PERRY

IPC: B22C9/04 ,  B22C7/02 ,  B22D25/06 ,  B22D27/20

Abstract: A method of manufacturing a component includes forming a mould assembly including an initial mould unit, providing a seed crystal including a primary growth direction, determining an optimal angular orientation of the unit, rotating the unit to dispose the unit's optimal angular orientation, encasing the unit in a refractory material, and forming a refractory mould unit having a component mould including a mould wall defining a mould cavity, and a seed holder. In the optimal angular orientation, the seed crystal's primary growth direction is angled away from the wall, thereby forming a converging disposition with the wall in a of the wall's first region facing the central sprue and a diverging disposition with the wall in the wall's second region facing a mould heater. The method includes receiving the seed crystal within the seed holder and filling the mould cavity with molten castable material to form the component.

公开(公告)号：US12158438B2

公开(公告)日：2024-12-03

申请号：US17853184

申请日：2022-06-29

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W Bemment ,  Paul W Ferra ,  Alastair G Hobday ,  Benjamin J Keeler ,  Kevin R Mcnally ,  Andrea Minelli ,  Martin K Yates

IPC: G01N25/22 ,  F02C7/22

Abstract: A method of checking refuelling of an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises: receiving an input of calorific value data for fuel provided to the aircraft on refuelling; independently determining at least one of: (i) the calorific value of fuel supplied to the gas turbine engine in use; and (ii) the calorific value of the fuel provided to the aircraft on refuelling; and providing an alert if the determined calorific value is inconsistent with the calorific value data input received.

公开(公告)号：US20240392970A1

公开(公告)日：2024-11-28

申请号：US18652125

申请日：2024-05-01

Applicant: ROLLS-ROYCE plc

Inventor： Stephen C. HARDING

IPC: F23R3/42 ,  F02C3/14

Abstract: A combustor assembly for a gas turbine engine comprises a combustor casing. The combustor casing has a diametral height D and an axial length L. An Aspect Ratio parameter S is defined as: S = D L and the S parameter lies in the range of 0.30 to 1.00.

公开(公告)号：US20240392855A1

公开(公告)日：2024-11-28

申请号：US18670836

申请日：2024-05-22

Applicant: ROLLS-ROYCE plc

Inventor： Victor P A MEDEAU ,  Silvestre T. PINHO ,  Lorenzo MENCATTELLI ,  Emile S. GREENHALGH ,  Soraia PIMENTA ,  MohammadErfan KAZEMI ,  James A. FINLAYSON

IPC: F16F7/00 ,  F01D5/28

Abstract: A kinetic energy absorptive composite article comprising a plurality of plies, and a method of manufacturing the kinetic energy absorptive composite article. Each ply comprises a plurality of substantially parallel fibers encapsulated within a resin. A plurality of localised weaknesses are comprised within the fibers of the kinetic energy absorptive composite article, the locations of the plurality of localised weaknesses forming a pre-defined pattern. The pre-defined pattern comprises a first sub-pattern and a second sub-pattern superposed upon the first sub-pattern. The first sub-pattern is configured so that a crack formed by an impact event propagates substantially along a predetermined fracture path to separate the kinetic energy absorptive composite article into at least a first portion and a second portion and the second sub-pattern is configured to set a threshold below which the crack does not propagate.

公开(公告)号：US12152542B2

公开(公告)日：2024-11-26

申请号：US18328991

申请日：2023-06-05

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  David M. Beaven ,  Craig W. Bemment ,  Alastair G. Hobday ,  Benjamin J. Keeler ,  Christopher P. Madden ,  Martin K. Yates

IPC: F02C9/40 ,  F02C9/28

Abstract: The present application provides a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft. The method includes: passing UV-visual spectrum light through the fuel; measuring a transmittance parameter indicating the transmittance of light through the fuel; determining one or more fuel characteristics of the fuel based on the transmittance parameter; and communicating the one or more fuel characteristic to a control module of the gas turbine engine or the aircraft. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

公开(公告)号：US20240384658A1

公开(公告)日：2024-11-21

申请号：US18646115

申请日：2024-04-25

Applicant: ROLLS-ROYCE plc

Inventor： Jonathon BAILEY ,  Basile VIGNERON

IPC: F01D9/04

Abstract: A single-piece annular vane array for a gas turbine engine. The single-piece annular vane array comprises at least one mounting feature, a ring of stator vanes, and at least one baffle. The at least one baffle is attached at a first radial location to the ring of stator vanes, and is attached at a second radial location to the at least one mounting feature. The at least one baffle is deformable.

公开(公告)号：US12135313B2

公开(公告)日：2024-11-05

申请号：US17958996

申请日：2022-10-03

Applicant: ROLLS-ROYCE plc

Inventor： Duncan A Macdougall ,  Julian M Reed ,  Sophoclis Patsias ,  Antonio Pellegrino ,  Clive R Siviour ,  Daniel Eakins ,  Yuan Xu ,  Junyi Zhou

IPC: G01N3/30 ,  G01N3/02

Abstract: A system for measuring loading on a test specimen. The system includes the test specimen arranged between a first loading bar and a second loading bar. The system further includes a first loading unit and a second loading unit configured to apply a first load and a second load to the first and second loading bars, respectively. The system further includes a first clamp and a second clamp configured to hold the first and second loading bars against the first and second loads, respectively. The system further includes a clamp actuating unit configured to selectively release at least the first clamp. The clamp actuating unit further includes a controller configured to electrically actuate at least one first electromechanical transducer from a retained state to a released state to release the first clamp, such that the first loading bar applies a first loading wave to the test specimen.

公开(公告)号：US20240361218A1

公开(公告)日：2024-10-31

申请号：US18647507

申请日：2024-04-26

Applicant: ROLLS-ROYCE plc

Inventor： Akhil MULLOTH

IPC: G01N1/42 ,  G01N23/046

CPC classification number: G01N1/42 ,  G01N23/046 ,  G01N2223/3103 ,  G01N2223/63

Abstract: A method for scanning at least one component includes placing the at least one component inside a storage vessel; filling the storage vessel with a cryogenic material; cooling the at least one component; placing the storage vessel between an x-ray source and a detector of a CT scanner; generating, via the x-ray source, an x-ray cone beam after cooling of the component that passes through the storage vessel while the at least one component is disposed within the storage vessel; receiving the x-ray cone beam at the detector; and generating an x-ray image of the at least one component.

公开(公告)号：US12123362B2

公开(公告)日：2024-10-22

申请号：US18225427

申请日：2023-07-24

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  Christopher P Madden ,  Craig W Bemment

IPC: F02C9/40 ,  F02C9/28 ,  F23R3/34

CPC classification number: F02C9/40 ,  F02C9/28 ,  F23R3/343 ,  F05D2220/323 ,  F05D2270/08 ,  F05D2270/306 ,  F05D2270/31 ,  F05D2270/71

Abstract: An aircraft has first and second fuel sources containing fuels with different characteristics, and one or more gas turbine engines powered by the fuels and each having a staged combustion system having pilot and main fuel injectors and being operable in pilot-only and pilot-and-main ranges of operation. The gas turbine engines each have a fuel delivery regulator arranged to control fuel delivery to the pilot and main fuel injectors. The method includes: obtaining a proposed mission description; obtaining nvPM impact parameters for the gas turbine engines, the impact parameters being associated with each operating condition of the proposed mission; calculating an optimised set of one or more fuel characteristics for each flight condition of the proposed flight defined in the flight description based on the nvPM impact parameters; and determining a fuel allocation based on the optimised set of one or more fuel characteristics.

公开(公告)号：US12123351B2

公开(公告)日：2024-10-22

申请号：US17484897

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

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

IPC: F02C7/18 ,  F01D25/12 ,  F02C7/04 ,  F02C7/143 ,  F02K3/065

CPC classification number: F02C7/18 ,  F01D25/12 ,  F02C7/04 ,  F02C7/143 ,  F02C7/185 ,  F02K3/065 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/36 ,  F05D2260/606

Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D), and the heat exchanger module comprises a plurality of heat exchanger elements. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, with the heat exchanger module having an axial length along a central axis between an upstream-most face of the heat exchanger elements and a downstream-most face of the heat exchanger elements. The axial length is in the range of 0.1*D to 5.0*D.