Gas turbine
    41.
    发明授权

    公开(公告)号:US11454174B2

    公开(公告)日:2022-09-27

    申请号:US17147762

    申请日:2021-01-13

    申请人: ROLLS-ROYCE PLC

    发明人: Alan R Maguire

    摘要: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a static structure on the input side of the gearbox device, an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device.

    Balanced circumferential seal
    42.
    发明授权

    公开(公告)号:US11448081B2

    公开(公告)日:2022-09-20

    申请号:US16657739

    申请日:2019-10-18

    IPC分类号: F01D11/00 F01D5/02 F02C7/28

    摘要: A machine has: an outer member; an inner member mounted for rotation about an axis relative to the outer member; and a seal system. The seal system has: a seal housing mounted to the outer member; one or more seal rings held by the seal housing and having an inner diameter surface; and a seal runner mounted to the inner member and having a first outer diameter surface portion contacting or facing the inner diameter surface of the one or more seal rings. The seal runner has a circumferential array of mounting features. One or more weights are mounted to one or more of the mounting features.

    PISTON RING SHUTTLE CARRIER
    43.
    发明申请

    公开(公告)号:US20220282631A1

    公开(公告)日:2022-09-08

    申请号:US17189487

    申请日:2021-03-02

    发明人: Fadi S. Maalouf

    IPC分类号: F01D11/00 F01D5/02

    摘要: A rotating assembly of a gas turbine engine includes a first rotating component; and a second rotating component located radially outboard of the first rotating component, relative to an engine central longitudinal axis. A seal assembly is configured to seal between the first rotating component and the second rotating component. The seal assembly includes a shuttle located on a radial outer surface of the second component and freely axially movable along the radial outer surface and a piston ring seal retained in the shuttle and engaged with the first rotating component. Axial motion of the first rotating component relative to the second rotating component urges movement of the shuttle along the radial outer surface of the second rotating component, while the position of the piston ring seal remains stationary relative to the first rotating component.

    INLET CONE FOR AN AIRCRAFT TURBINE ENGINE AND ASSOCIATED AIRCRAFT TURBINE ENGINE

    公开(公告)号:US20220235670A1

    公开(公告)日:2022-07-28

    申请号:US17596405

    申请日:2020-06-04

    摘要: The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

    BALANCING WEIGHT ENTRY PORT FOR TURBINE ROTOR

    公开(公告)号:US20220220853A1

    公开(公告)日:2022-07-14

    申请号:US17657409

    申请日:2022-03-31

    IPC分类号: F01D5/02 B23C3/18

    摘要: A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body and aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body that is smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.

    Feedback device with differing magnetic permeability zones

    公开(公告)号:US11371825B2

    公开(公告)日:2022-06-28

    申请号:US16739052

    申请日:2020-01-09

    摘要: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and having an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device comprising a non-magnetically permeable body defining a root surface and a plurality of magnetically permeable position markers circumferentially disposed on the root surface, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.

    Aerofoil assembly and method
    50.
    发明授权

    公开(公告)号:US11371356B2

    公开(公告)日:2022-06-28

    申请号:US17149142

    申请日:2021-01-14

    申请人: ROLLS-ROYCE PLC

    IPC分类号: F01D5/14 F01D5/02

    摘要: An aerofoil assembly includes a platform and a plurality of aerofoils extending radially outward from the platform. The platform has a first edge, a second edge, and a platform surface disposed between the first edge and the second edge. Each aerofoil has a leading edge proximal to the first edge and a trailing edge distal to the first edge. A pitch spacing is defined between the leading edges of adjacent aerofoils along the platform surface. A mid-pitch location is defined midway along the pitch spacing. The platform defines one or more recesses disposed between the leading edges of the plurality of aerofoils and the first edge. Each of the one or more recesses is disposed proximal to the mid-pitch location between adjacent aerofoils.