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    Turbine blade for a gas turbine engine
    111.
    发明授权
    Turbine blade for a gas turbine engine 有权

    公开(公告)号：US11879357B2

    公开(公告)日：2024-01-23

    申请号：US18067961

    申请日：2022-12-19

    Applicant: ROLLS-ROYCE plc

    Inventor： Peter T. Ireland ,  John Coull ,  João António Coelho Vieira

    IPC: F01D5/18 ,  F01D25/12

    CPC classification number: F01D5/186 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2260/202

    Abstract: A turbine blade includes an aerofoil including a leading edge, a trailing edge, a first sidewall, a second sidewall, and an internal cooling circuit disposed within the aerofoil and configured to direct a cooling fluid within the aerofoil. The turbine blade includes at least one first recessed portion formed on the first sidewall proximal to a tip of the turbine blade. The first recessed portion is disposed proximal to and spaced apart from the trailing edge of the aerofoil. The first recessed portion includes a base surface, a first surface, and a second surface. The first recessed portion further includes at least one slot extending from the first surface to the internal cooling circuit. The slot is configured to allow a flow of the cooling fluid from the internal cooling circuit to the first recessed portion.

    GAS TURBINE ENGINE
    115.
    发明公开
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20240011433A1

    公开(公告)日：2024-01-11

    申请号：US18215868

    申请日：2023-06-29

    Applicant: ROLLS-ROYCE plc

    Inventor： Stephen J. BRADBROOK ,  William J. SMITH ,  Jonathan P. BRADLEY

    IPC: F02C3/06

    CPC classification number: F02C3/06 ,  F05D2220/36

    Abstract: A novel configuration for axial flow gas turbine engine for aircraft has an engine core having a core length and including first turbine, axial compressor, and drive connecting the first turbine to the axial compressor, the engine core further including a second turbine, and a fan shaft connecting the second turbine to a fan located upstream of the engine core, the fan including a plurality of fan blades extending from a fan hub, the fan having a tip radius from 90 mm to 225 mm and wherein the ratio of fan tip radius to an engine length is 0.15 to 0.25. The engine may have 3, 4 or 5 compressor stages and a combustor volume (in litres) which when divided by the fan tip radius (in mm) is 0.015 to 0.083. The fan may be a multistage fan configured to permit an electric motor to be located within the fan hub diameter.

    Storage tank for liquid hydrogen
    116.
    发明授权
    Storage tank for liquid hydrogen 有权

    公开(公告)号：US11859765B2

    公开(公告)日：2024-01-02

    申请号：US17825329

    申请日：2022-05-26

    Applicant: ROLLS-ROYCE plc

    Inventor： Robert C. Backhouse

    IPC: F17C1/12

    CPC classification number: F17C1/12 ,  F17C2203/012 ,  F17C2203/0607 ,  F17C2203/0631 ,  F17C2203/0673 ,  F17C2221/012 ,  F17C2260/013 ,  F17C2270/0189

    Abstract: A storage tank for liquid hydrogen comprises first and second shells each constructed of laminate material, the second shell being disposed outwardly of the first shell with respect to the centre of the storage tank. The first and second shells are mechanically connected by a first plurality of pins each of which passes through at least some layers of the second shell and at least some layers of the first shell. The storage tank may be constructed using a simpler manufacturing process involving less tooling and fewer process steps than is the case for known tanks for storing liquid hydrogen. The storage tank has also has a lower mass and reduced thermal losses compared to tanks of the prior art. The plurality of pins allows for the shells to be thinner, and hence lighter, than similar shells in tanks of the prior art.

    Joint assembly
    117.
    发明授权
    Joint assembly 有权

    公开(公告)号：US11852185B2

    公开(公告)日：2023-12-26

    申请号：US17064895

    申请日：2020-10-07

    Applicant: ROLLS-ROYCE PLC

    Inventor： David R Coles ,  Daniel Clark

    IPC: F16B7/04 ,  F16B5/00

    CPC classification number: F16B5/0088 ,  F16B7/0406

    Abstract: A joint assembly joins first and second components about a common axis. The first component has a first end portion having a radially outwardly facing surface shaped to fit radially inside a second surface of a hollow second end portion of the second component to form an interface between the opposing first and second surfaces. The first and second surfaces have a concavity extending laterally with respect to the axis such that when the first and second surfaces are opposingly arranged the opposing concavities define a cavity at the interface. A retaining member is insertable into the cavity at the interface to prevent axial separation of the first and second components. One of the first and second end portions has a free end protrusion axially spaced from the concavity and the other of the first and second end portions has an axially extending recess arranged to receive the free end.

    REPAIR SYSTEM AND METHOD FOR IN-SITU REPAIR OF MACHINE
    118.
    发明公开
    REPAIR SYSTEM AND METHOD FOR IN-SITU REPAIR OF MACHINE 审中-公开

    公开(公告)号：US20230398632A1

    公开(公告)日：2023-12-14

    申请号：US18322916

    申请日：2023-05-24

    Applicant: ROLLS-ROYCE plc

    Inventor： Adam CLARE ,  Andres A. GAMEROS MADRIGAL ,  James KELL ,  Andrew D. NORTON ,  Thomas GIRERD

    IPC: B23K26/26 ,  B23P6/00

    CPC classification number: B23K26/26 ,  B23P6/00

    Abstract: A repair system for in-situ repair of a machine. The repair system includes a laser unit configured to emit a laser beam, a galvanometer optically coupled to the laser unit and configured to adjust the laser beam received from the laser unit, a source of a flexible metallic mesh, a delivery unit configured to receive the flexible metallic mesh from the source of the flexible metallic mesh, and a controller communicably coupled to the laser unit, the galvanometer, and the delivery unit. The controller is configured to control the delivery unit to deposit the flexible metallic mesh on a surface of the machine. The controller is further configured to control the laser unit to emit the laser beam and to control the galvanometer to adjust the laser beam in order to weld the flexible metallic mesh to the surface of the machine, thereby forming a repair patch.

    Aircraft engine
    119.
    发明授权
    Aircraft engine 有权

    公开(公告)号：US11840965B2

    公开(公告)日：2023-12-12

    申请号：US17980230

    申请日：2022-11-03

    Applicant: ROLLS-ROYCE plc

    Inventor： Mark Spruce

    IPC: F02C7/36 ,  F16H1/28 ,  F16H57/02

    CPC classification number: F02C7/36 ,  F16H1/28 ,  F16H2057/02039

    Abstract: A gas turbine engine for an aircraft configured with an engine core that has a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, that has a plurality of fan blades. A gearbox arranged to receive an input from the core shaft and to output to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The gearbox having an overall gear mesh stiffness, and wherein the overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m and less than or equal to 8.0×109 N/m.

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