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    Geared gas turbine engine
    1.
    发明授权
    Geared gas turbine engine 有权

    公开(公告)号：US11781491B2

    公开(公告)日：2023-10-10

    申请号：US17987516

    申请日：2022-11-15

    Applicant: ROLLS-ROYCE plc

    Inventor： Nicholas Howarth ,  Gareth M Armstrong

    IPC: F01D15/12 ,  F02C7/36 ,  F02C3/113

    CPC classification number: F02C7/36 ,  F01D15/12 ,  F02C3/113

    Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

    Dynamic sealing assembly
    3.
    发明授权
    Dynamic sealing assembly 有权

    公开(公告)号：US12084976B2

    公开(公告)日：2024-09-10

    申请号：US18463633

    申请日：2023-09-08

    Applicant: Rolls-Royce plc

    Inventor： Christopher A. Murray ,  Nicholas Howarth

    IPC: F01D11/00 ,  F01D15/08 ,  F01D17/14

    CPC classification number: F01D11/001 ,  F01D15/08 ,  F01D17/143 ,  F05D2240/56

    Abstract: There is provided a dynamic sealing assembly for a rotary machine, comprising a primary sandwich plate, a secondary sandwich plate and a bristle pack. The primary sandwich plate comprises a plurality of primary vane openings, and the secondary sandwich plate comprises a plurality of secondary vane openings. The bristle pack comprises a plurality of bristles and is disposed between the primary sandwich plate and the secondary sandwich plate. Each of the plurality of primary vane openings overlies and aligns with a respective secondary vane opening to form a vane channel for receiving a vane along a longitudinal axis of the dynamic sealing assembly. The bristle pack is configured to: provide a brush seal between each vane received within the respective vane channels and the dynamic sealing assembly; and allow relative movement between the dynamic sealing assembly and the vane received within each vane channel along the longitudinal axis.

    Air intake guide
    4.
    发明授权
    Air intake guide 有权

    公开(公告)号：US09631555B2

    公开(公告)日：2017-04-25

    申请号：US14221936

    申请日：2014-03-21

    Applicant: ROLLS-ROYCE PLC

    Inventor： Nicholas Howarth

    IPC: F02C7/057 ,  F02C7/042

    CPC classification number: F02C7/057 ,  F02C7/042 ,  F05D2220/80 ,  F05D2250/141 ,  F05D2260/407 ,  F05D2300/501 ,  Y02T50/672 ,  Y10T137/0379 ,  Y10T137/0536 ,  Y10T137/0645

    Abstract: An air intake guide for a jet propulsion power plant for a supersonic aircraft comprises an intake aperture, an intake center body and an intake adjustment device. The intake aperture has an intake lip, an intake center body is positioned within the aperture, and an intake adjustment device is positioned on a radially inwardly facing surface of the air intake guide downstream of the intake lip. The intake adjustment device comprises a flexible panel and an actuator with the actuator being adapted to deflect the flexible panel in a radially inwardly direction so as to reduce a cross-sectional area of the intake aperture and thereby to position a shock wave at the intake lip.

    Gas turbine engine
    5.
    发明授权
    Gas turbine engine 有权
    燃气轮机

    公开(公告)号：US09387923B2

    公开(公告)日：2016-07-12

    申请号：US13914882

    申请日：2013-06-11

    Applicant: ROLLS-ROYCE PLC

    Inventor： Richard Geoffrey Stretton ,  Nicholas Howarth

    IPC: B64C11/00 ,  F02C3/067

    CPC classification number: B64C11/001 ,  B64D27/00 ,  B64D2027/005 ,  F02C3/067 ,  F02C7/04 ,  F02C7/05 ,  F02K3/025 ,  F02K3/04 ,  F05D2220/323 ,  F05D2220/325 ,  F05D2240/302 ,  F05D2250/324 ,  F05D2250/51 ,  Y02T50/66 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine engine (10) having an axial flow direction (X) therethrough in use. The gas turbine engine (10) comprises one or more rotor stages each comprising at least one rotor blade (120) having a root portion (122). The gas turbine engine (10) comprises a shroud (122) located upstream of one or more of the rotor stages relative to the axial flow direction (X). The shroud (122) defines a through passageway (128) extending between an inlet (130) and an outlet (132) which comprises a diffuser region (138). The diffuser region (138) is configured to reduce the axial velocity of air exiting the outlet (132) relative to air entering the diffuser portion (138) in use, wherein the outlet (132) is located such that air exiting the outlet (132) is directed substantially to the root portion (122) only of the rotor blades (120).

    Abstract translation: 一种在使用中具有轴流动方向（X）的燃气轮机（10）。 燃气涡轮发动机（10）包括一个或多个转子级，每个转子级包括至少一个具有根部（122）的转子叶片（120）。 燃气涡轮发动机（10）包括相对于轴向流动方向（X）定位在一个或多个转子级的上游的护罩（122）。 护罩（122）限定在入口（130）和包括扩散器区域（138）的出口（132）之间延伸的通道（128）。 扩散器区域（138）构造成在使用时相对于进入扩散器部分（138）的空气减少离开出口（132）的空气的轴向速度，其中出口（132）定位成使得离开出口（132）的空气 ）仅基本上指向转子叶片（120）的根部（122）。

    Compressor variable angle measurement system
    6.
    发明授权
    Compressor variable angle measurement system 有权

    公开(公告)号：US11933634B2

    公开(公告)日：2024-03-19

    申请号：US17818818

    申请日：2022-08-10

    Applicant: ROLLS-ROYCE plc

    Inventor： Nicholas Howarth

    IPC: G01C9/00 ,  F04D27/02 ,  G01B7/30

    CPC classification number: G01C9/005 ,  F04D27/0246 ,  G01B7/30 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2270/80

    Abstract: A compressor variable angle measurement system for guiding the positioning variable vanes supported on a penny of a compressor of a gas turbine engine. The system comprising a gauge assembly that is connectable to a computing device. the gauge assembly comprises a base plate and a clamp arm. The gauge assembly is configured to removably grip a variable vane between three vane contact portions of the baseplate and the vane contact portion of the clamp arm and on the leading edge vane engaging portion and the trailing edge vane engaging portion of the base plate, the stagger angle of the variable vane with respect to the radial setting pin being determined by the computing device from measurements made by an inertial measurement unit.

    Geared gas turbine engine
    7.
    发明授权
    Geared gas turbine engine 有权

    公开(公告)号：US11346287B2

    公开(公告)日：2022-05-31

    申请号：US17171439

    申请日：2021-02-09

    Applicant: ROLLS-ROYCE PLC

    Inventor： Nicholas Howarth ,  Gareth M Armstrong

    IPC: F02C7/36 ,  F02C3/113 ,  F01D15/12

    Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

    Blower system
    8.
    发明授权
    Blower system 有权

    公开(公告)号：US12172757B2

    公开(公告)日：2024-12-24

    申请号：US18155351

    申请日：2023-01-17

    Applicant: ROLLS-ROYCE plc ,  Rolls-Royce Corporation

    Inventor： Christopher A. Murray ,  Nicholas Howarth ,  Daniel Swain ,  Ian J. Bousfield

    IPC: B64D13/06 ,  F02C7/32 ,  F04D25/04 ,  F04D29/68

    Abstract: There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.

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