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    GAS TURBINE ENGINE MOUNTING ARRANGEMENT
    1.
    发明申请
    GAS TURBINE ENGINE MOUNTING ARRANGEMENT 审中-公开

    公开(公告)号：US20200049022A1

    公开(公告)日：2020-02-13

    申请号：US16507231

    申请日：2019-07-10

    Applicant: ROLLS-ROYCE plc

    Inventor： Richard G. STRETTON ,  Steven A. RADOMSKI

    IPC: F01D9/04 ,  F02K3/06

    Abstract: A gas turbine engine (10) comprises a bypass duct cowl (21), an engine core housing (22) defining an engine core inlet, a bypass fan (13) and a plurality of outlet guide vanes (24). Each outlet guide vane 24 extends between a radially inner surface of the bypass duct cowl (21) and a radially outer surface of the engine core housing (22, 23) to define an outlet guide vane span (SPANOGV). The outlet guide vanes (24) are configured to support the engine core housing (22, 23) relative to the bypass duct cowl (21). The bypass fan (13) and an engine core inlet (34) define a bypass ratio between 10 and 17, and a ratio of the outlet guide vane span (OGVSPAN) to a bypass fan radius (RFAN) is between 0.45 and 0.55.

    GAS TURBINE ENGINE COWL DOORS
    3.
    发明申请
    GAS TURBINE ENGINE COWL DOORS 有权

    公开(公告)号：US20210079810A1

    公开(公告)日：2021-03-18

    申请号：US16909060

    申请日：2020-06-23

    Applicant: ROLLS-ROYCE plc

    Inventor： Richard G. STRETTON ,  Steven A. RADOMSKI

    IPC: F01D25/24

    Abstract: A gas turbine engine casing is described as having a cowl door hinged to a casing support structure by at least one hinge. The cowl door is openable outwardly from the casing to expose a casing interior. The hinge is located above a longitudinal axis of the casing and comprises a pivoting linkage arranged such that, upon actuation between closed and open cowl door conditions, the pivoting linkage moves an upper portion of the cowl door downwards towards the longitudinal axis.

    SEAL ASSEMBLY
    4.
    发明申请
    SEAL ASSEMBLY 审中-公开

    公开(公告)号：US20200317354A1

    公开(公告)日：2020-10-08

    申请号：US16832607

    申请日：2020-03-27

    Applicant: ROLLS-ROYCE plc

    Inventor： Steven A. RADOMSKI ,  Richard G. STRETTON

    IPC: B64D27/26 ,  F16J15/10

    Abstract: A seal assembly for a gas turbine engine having a rotor arranged to rotate about an axis in use. The seal assembly has a static support structure for the gas turbine engine and a casing structure of the engine. Rotation of the engine rotor causes a deflection of the casing structure relative to the static support structure in a first direction. A seal is provided at an interface between the static support structure and the casing structure, and comprising a first seal portion and a second seal portion spaced from one another in the first direction. The first seal portion is provided against a first surface of the casing structure and the second seal portion is provided against a second surface of the casing structure opposing the first surface. In an at-rest state in which the engine is not operational, the first and second surfaces are offset from an equilibrium position with respect to the static support structure such that there is a difference in compression of the first seal portion and the second seal portion between the static support structure and the casing structure. The offset is in a direction opposite to the first direction.

    FAN CASING ARRANGEMENT FOR A GAS TURBINE ENGINE
    6.
    发明申请
    FAN CASING ARRANGEMENT FOR A GAS TURBINE ENGINE 审中-公开
    气体涡轮发动机风扇安装

    公开(公告)号：US20160169043A1

    公开(公告)日：2016-06-16

    申请号：US14941095

    申请日：2015-11-13

    Applicant: ROLLS-ROYCE PLC

    Inventor： Simon READ ,  Steven A. RADOMSKI

    IPC: F01D25/24 ,  F01D11/12 ,  F01D21/04

    CPC classification number: F01D25/24 ,  F01D11/125 ,  F01D11/127 ,  F01D21/045 ,  F04D29/522 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/55 ,  F05D2250/283 ,  F05D2260/37 ,  F05D2300/43 ,  F05D2300/501 ,  F05D2300/603

    Abstract: There is proposed a fan casing arrangement for a gas turbine engine (10) of a type having a propulsive fan (12), the fan casing arrangement being configured to circumscribe the fan (12) and having a fan case (24) and a fan track liner. The fan track liner is provided around the inside of the fan case (24) so as to adopt a radial position between the fan (12) and the fan case (24), and the arrangement is configured such that the fan track liner includes a liner ring (25) which is radially outwardly biased against the inside of the fan case (24). A related method of installing a fan track liner in a gas turbine engine is also disclosed.

    Abstract translation: 提出了一种用于具有推进风扇（12）类型的燃气涡轮发动机（10）的风扇壳体装置，风扇壳体装置被配置为围绕风扇（12）并具有风扇壳体（24）和风扇 轨道班轮 风扇导轨衬套设置在风扇壳体24的内部周围，以便在风扇12和风扇壳体24之间采用径向位置，并且该结构构造成使得风扇履带衬板包括一个 衬套环（25），其径向向外偏压抵靠风扇壳体（24）的内部。 还公开了一种在燃气涡轮发动机中安装风扇轨道衬套的相关方法。

    VANE ARRANGEMENT FOR A GAS TURBINE ENGINE
    7.
    发明申请
    VANE ARRANGEMENT FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20180318966A1

    公开(公告)日：2018-11-08

    申请号：US15969178

    申请日：2018-05-02

    Applicant: ROLLS-ROYCE plc

    Inventor： Dale E. EVANS ,  Steven A. RADOMSKI ,  Clive GRAFTON-REED

    IPC: B23K31/02 ,  F01D9/04

    Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub with a through hole extending therethrough. The method comprises welding the aerofoil to the stub such that the open end of the hollow cavity of the aerofoil is aligned with the through hole of the stub so as to define a hollow region extending through the support member and stub to the cavity of the aerofoil. During welding a tool is positioned within the through hole and cavity and is aligned with an interface between the stub and aerofoil, the tool being configured to prevent weld splatter onto a surface of the cavity or through hole.

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