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    AERODYNAMIC FAIRINGS SECONDARILY ATTACHED TO NOSECONE
    3.
    发明申请
    AERODYNAMIC FAIRINGS SECONDARILY ATTACHED TO NOSECONE 有权
    二次连接到NOSECONE的AERODYNAMIC FAIRINGS

    公开(公告)号：US20140255204A1

    公开(公告)日：2014-09-11

    申请号：US14035571

    申请日：2013-09-24

    Applicant: Rolls-Royce Corporation

    Inventor： Trevor John Totten ,  Jonathan Michael Rivers ,  Eric William Engebretsen

    IPC: B64C11/14

    CPC classification number: B64C11/14 ,  F01D5/066 ,  F02C7/04 ,  F02K3/06 ,  F05D2300/603 ,  Y10T29/49336 ,  Y10T156/10

    Abstract: An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy. The fairings may be secured to the nosecone by various methods, including providing for the fairings to be changed out and replaced with other fairings on the same nosecone assembly.

    Abstract translation: 提供了一种用于燃气涡轮发动机的空气动力学风扇叶片，并且包括可由复合材料制成的风扇叶片。 为了改善到叶片构件的气流过渡，提供了空气动力学整流罩并且固定到鼻锥的外表面，这提高了燃料经济性。 整流罩可以通过各种方法固定在鼻锥上，包括将整流罩放置在同一个鼻锥组件上的其他整流罩上。

    GAS TURBINE ENGINE BLADE AND DISK
    4.
    发明申请
    GAS TURBINE ENGINE BLADE AND DISK 有权
    气体涡轮发动机叶片和盘

    公开(公告)号：US20140241890A1

    公开(公告)日：2014-08-28

    申请号：US14133140

    申请日：2013-12-18

    Applicant: Rolls-Royce Corporation

    Inventor： Roy David Fulayter ,  Jonathan Michael Rivers

    IPC: F01D5/30 ,  B23P15/02

    CPC classification number: F01D5/3061 ,  B23K20/12 ,  B23P15/02 ,  F01D5/005 ,  F01D5/34 ,  F05D2230/239 ,  Y10T29/49318 ,  Y10T29/49336

    Abstract: In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface.

    Abstract translation: 在一些示例中，装置可以包括燃气涡轮发动机部件，其包括叶片，形成气流表面的平台，刀片从一侧延伸出来，以及设置在平台的非气流侧的运动焊接接收表面，以及 具有运动焊接盘部分的盘，用于接收燃气涡轮发动机部件的运动焊接接收表面，并且当盘和燃气涡轮发动机部件联接时形成运动焊接耦合，其中，在耦合之前，燃气涡轮发动机部件进一步 包括设置在所述平台的非气流侧的叶片杆，并且其中形成有所述运动焊接接收表面。

    COMPOSITE AEROFOILS
    5.
    发明申请
    COMPOSITE AEROFOILS 有权

    公开(公告)号：US20210355833A1

    公开(公告)日：2021-11-18

    申请号：US15930158

    申请日：2020-05-12

    Applicant: Rolls-Royce Corporation

    Inventor： Robert Heeter ,  Matthew J. Kappes ,  Jonathan Michael Rivers ,  Benedict N. Hodgson

    IPC: F01D5/28 ,  F01D9/02

    Abstract: A composite aerofoil may include an aerofoil body defining a leading edge and a trailing edge, wherein the body comprises a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements. The disclosure also describes techniques for forming composite aerofoils.

    Aerodynamic fairings secondarily attached to nosecone
    8.
    发明授权
    Aerodynamic fairings secondarily attached to nosecone 有权
    气动整流罩二次附于诺斯科

    公开(公告)号：US09481448B2

    公开(公告)日：2016-11-01

    申请号：US14035571

    申请日：2013-09-24

    Applicant: Rolls-Royce Corporation

    Inventor： Trevor John Totten ,  Jonathan Michael Rivers ,  Eric William Engebretsen

    IPC: B64C11/14 ,  F01D5/06 ,  F02C7/04

    CPC classification number: B64C11/14 ,  F01D5/066 ,  F02C7/04 ,  F02K3/06 ,  F05D2300/603 ,  Y10T29/49336 ,  Y10T156/10

    Abstract: An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy. The fairings may be secured to the nosecone by various methods, including providing for the fairings to be changed out and replaced with other fairings on the same nosecone assembly.

    Abstract translation: 提供了一种用于燃气涡轮发动机的空气动力学风扇叶片，并且包括可由复合材料制成的风扇叶片。 为了改善到叶片构件的气流过渡，提供了空气动力学整流罩并且固定到鼻锥的外表面，这提高了燃料经济性。 整流罩可以通过各种方法固定在鼻锥上，包括将整流罩放置在同一个鼻锥组件上的其他整流罩上。

    FAN TRACK LINER DESIGNED TO YIELD NEXT TO FAN CASE HOOK
    9.
    发明申请
    FAN TRACK LINER DESIGNED TO YIELD NEXT TO FAN CASE HOOK 审中-公开
    风扇跟踪设计为风扇下一个风扇箱钩

    公开(公告)号：US20140255152A1

    公开(公告)日：2014-09-11

    申请号：US14019272

    申请日：2013-09-05

    Applicant: Rolls-Royce Corporation

    Inventor： Trevor John Totten ,  Jonathan Michael Rivers ,  Eric William Engebretsen ,  Matthew Joseph Kappes

    IPC: F01D25/24

    CPC classification number: F01D25/24 ,  F01D11/122 ,  F01D21/045 ,  F02K3/06 ,  F05D2220/36 ,  F05D2250/283 ,  F05D2300/702 ,  Y02T50/672

    Abstract: A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure. Various configurations of the fan track liner assembly are provided along with various mounting methodologies for securing the track liner assembly to the fan case of a gas turbine engine.

    Abstract translation: 用于燃气涡轮发动机的容纳系统包括与容纳壳体一起使用的风扇轨道组件。 风扇轨道组件包括位于风扇壳体的空腔内的可折叠材料体，并且在发生灾难性叶片故障的情况下提供空隙以提供空间。 提供了风扇轨道衬套组件的各种构造以及用于将轨道衬套组件固定到燃气涡轮发动机的风扇壳体的各种安装方法。

    Composite liners for turbofan engines
    10.
    发明授权
    Composite liners for turbofan engines 有权

    公开(公告)号：US11506083B2

    公开(公告)日：2022-11-22

    申请号：US16891928

    申请日：2020-06-03

    Applicant: Rolls-Royce Corporation

    Inventor： Matthew J. Kappes ,  Robert Heeter ,  Jonathan Michael Rivers ,  Benedict N. Hodgson

    IPC: F01D25/24 ,  F01D21/04 ,  F01D25/00 ,  F02C7/045

    Abstract: Composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

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