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    GAS TURBINE ENGINE AND TURBINE ARRANGEMENT
    2.
    发明申请
    GAS TURBINE ENGINE AND TURBINE ARRANGEMENT 审中-公开

    公开(公告)号：US20190309681A1

    公开(公告)日：2019-10-10

    申请号：US16352014

    申请日：2019-03-13

    Applicant: ROLLS-ROYCE plc

    Inventor： Roderick M. TOWNES ,  Keith C. SADLER

    IPC: F02C3/13 ,  F02C7/36 ,  F02C3/10 ,  F02C7/268 ,  F02K3/06 ,  F02C9/16

    Abstract: A turbine arrangement for gas turbine engine, the arrangement comprising a high pressure turbine mounted on a high pressure shaft and a low pressure turbine mounted on a low pressure shaft, wherein the high pressure turbine comprises a single stage turbine rotor configured to rotate in a first direction, and wherein the low pressure turbine comprises three or more rotors (19a, b, c) configured to rotate in a second direction opposite to the first direction. The low pressure turbine is closely coupled to the high pressure turbine with no stator vanes provided between the two.

    SHROUDED TURBINE BLADE
    3.
    发明申请
    SHROUDED TURBINE BLADE 审中-公开

    公开(公告)号：US20170130588A1

    公开(公告)日：2017-05-11

    申请号：US15343025

    申请日：2016-11-03

    Applicant: ROLLS-ROYCE plc

    Inventor： Roderick M. TOWNES

    IPC: F01D5/14 ,  F01D5/18 ,  F01D25/32 ,  F01D11/08

    CPC classification number: F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D5/225 ,  F01D11/08 ,  F01D25/32 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/307 ,  F05D2240/55 ,  F05D2240/81 ,  F05D2260/20

    Abstract: A shrouded turbine blade including a blade body having an operationally upstream face, an operationally downstream face, a root end and a tip end and a shroud segment provided at the tip end, the blade having an inlet in the root end and a cooling passage passing from the inlet to the tip end, the shroud segment comprising an arcuate platform and a seal fin arranged towards an operationally upstream end of the shroud platform and extending away from the blade body and circumferentially across the shroud platform, a fin cooling passage in fluid communication with the tip end of the blade cooling passage, the fin cooling passage having at least one outlet on an operationally downstream facing side of the fin, and a flow discourager arranged towards an operationally downstream end of the shroud platform.

    GAS TURBINE ENGINE
    4.
    发明申请
    GAS TURBINE ENGINE 有权

    公开(公告)号：US20240426251A1

    公开(公告)日：2024-12-26

    申请号：US18825435

    申请日：2024-09-05

    Applicant: ROLLS-ROYCE plc

    Inventor： Pascal DUNNING ,  Roderick M. TOWNES ,  Michael J. WHITTLE

    IPC: F02C7/36 ,  F01D5/28 ,  F01D5/30 ,  F02C3/073

    Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

    GAS TURBINE ENGINE
    8.
    发明申请
    GAS TURBINE ENGINE 有权

    公开(公告)号：US20210207528A1

    公开(公告)日：2021-07-08

    申请号：US17209989

    申请日：2021-03-23

    Applicant: ROLLS-ROYCE PLC

    Inventor： Pascal DUNNING ,  Roderick M. TOWNES ,  Michael J. WHITTLE

    IPC: F02C3/073 ,  F02C7/36 ,  F01D5/28 ,  F01D5/30

    Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

    COOLED TURBINE ROTOR BLADE
    9.
    发明申请
    COOLED TURBINE ROTOR BLADE 审中-公开

    公开(公告)号：US20200263553A1

    公开(公告)日：2020-08-20

    申请号：US16700335

    申请日：2019-12-02

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

    Inventor： Hamish SWEIDAN ,  Keith C. SADLER ,  Roderick M. TOWNES

    IPC: F01D5/18 ,  F01D5/08

    Abstract: A cooled turbine rotor blade for a gas turbine engine includes an airfoil and a profiled root radially inward of the airfoil, a platform between the airfoil and the root, and a cooling air supply channel extending through the platform into an interior of the airfoil and therein up to an outlet opening. An inlet opening of the cooling air supply channel is located at the rear side of the rotor blade, and an inlet part of the cooling air supply channel with the inlet opening is angled into the direction of rotation of the rotor blade and curved into a radially outward direction. Further, a rotor-stator stage for a gas turbine includes a rotor blade as above, and an air cavity radially inwards of sealing features between the rotor stage and a neighboring downstream stator stage to form a source of cooling air for the rotor blade.

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