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    ADJUSTABLE ENGINE MOUNT
    1.
    发明申请
    ADJUSTABLE ENGINE MOUNT 审中-公开
    可调发动机座

    公开(公告)号：WO2014021966A2

    公开(公告)日：2014-02-06

    申请号：PCT/US2013039818

    申请日：2013-05-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SANDY DAVID F ,  ZHENG ZHIJUN

    IPC: F02C7/20 ,  B64D27/10

    CPC classification number: F01D25/28 ,  B64D2027/262 ,  B64D2027/266 ,  B64D2027/268 ,  F02C7/20 ,  Y02T50/671

    Abstract: A forward engine mount assembly for a gas turbine engine includes a mount beam having a main body with a fore end and an aft end and a forward shackle assembly supported by the fore end of the mount beam. The forward shackle assembly comprises a first link configured to be connected to a first engine case structure and a second link configured to be connected to a second engine case structure. The first and second links are pivotally attached to each other.

    Abstract translation: 用于燃气涡轮发动机的前置发动机支架组件包括安装梁，该安装梁具有带前端和后端的主体以及由安装梁的前端支撑的前向卸扣组件。 前卸扣组件包括构造成连接到第一发动机壳体结构的第一连杆和构造成连接到第二发动机壳体结构的第二连杆。 第一和第二连杆彼此枢转地连接。

    SECONDARY LOAD PATH FOR GAS TURBINE ENGINE
    3.
    发明申请
    SECONDARY LOAD PATH FOR GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的二次负载路径

    公开(公告)号：WO2014042774A3

    公开(公告)日：2014-07-17

    申请号：PCT/US2013052833

    申请日：2013-07-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZHENG ZHIJUN ,  SANDY DAVID F

    IPC: F02C7/32 ,  B64D27/12 ,  F02C7/00

    CPC classification number: B64D27/26 ,  B64D2027/266 ,  Y02T50/44

    Abstract: A waiting link to support an engine on an aircraft includes a body portion including a first body portion opening, a second body portion opening, and a space therebetween. A first bearing is received in the first body portion opening and moveable in a generally vertical direction. A second bearing is received in the second body portion opening. The first and second bearings include a first and second bearing opening, respectively, that receives a first and second attachment member, respectively, that secures the body portion to a first and second structure, respectively. A cam is located in the space. The cam is pivotable between a first position and a second position. The waiting link does not provide a load path when the cam is in the first position, and when a primary load path fails, the waiting link provides the load path when the cam is in the second position.

    Abstract translation: 用于支撑飞机上的发动机的等待连接器包括主体部分，其包括第一主体部分开口，第二主体部分开口以及它们之间的空间。 第一轴承被容纳在第一主体部分中，并且在大致垂直的方向上可移动。 第二轴承被容纳在第二主体部分开口中。 第一和第二轴承分别包括第一和第二轴承开口，第一和第二轴承开口分别容纳分别将主体部分固定到第一和第二结构的第一和第二附接构件。 一个凸轮位于空间中。 凸轮可在第一位置和第二位置之间枢转。 当凸轮处于第一位置时，等待链接不提供负载路径，当主负载路径发生故障时，当凸轮处于第二位置时，等待连​​接提供负载路径。

    GAS TURBINE ENGINE MOUNTING STRUCTURE WITH SECONDARY LOAD PATHS
    4.
    发明专利
    GAS TURBINE ENGINE MOUNTING STRUCTURE WITH SECONDARY LOAD PATHS 未知

    公开(公告)号：SG11201404043YA

    公开(公告)日：2014-10-30

    申请号：SG11201404043Y

    申请日：2013-02-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZHENG ZHIJUN ,  SANDY DAVID F

    IPC: B64D27/00 ,  B64D27/40

    Abstract: A connection for mounting an aircraft engine to an aircraft pylon includes a plate to be connected to a portion of an engine, and a body that extends rearward from the plate. A back-up connection, including a pin positioned within a slotted hole, is provided between the portion of the engine and the body. When there is a normal connection between the plate and the body, there is clearance between the pin and the slotted hole.

    ASSEMBLY FOR MOUNTING A TURBINE ENGINE TO A PYLON
    5.
    发明公开
    ASSEMBLY FOR MOUNTING A TURBINE ENGINE TO A PYLON 审中-公开
    安排用于保护涡轮发动机上PYLON

    公开(公告)号：EP2893172A4

    公开(公告)日：2016-06-01

    申请号：EP13833645

    申请日：2013-09-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SANDY DAVID F ,  ZHENG ZHIJUN ,  DAILEY STEPHEN P ,  FOSTER JOSEPH P

    IPC: F02C7/32 ,  B64D27/26 ,  F02C7/36 ,  F02K3/06

    CPC classification number: B64D27/26 ,  B64D2027/266 ,  B64D2027/268 ,  F02C7/20 ,  F02K3/06

    Abstract: An assembly for mounting a turbine engine to a pylon includes a mounting beam, a plurality of fasteners, a first mounting linkage and a second mounting linkage. The mounting beam includes a mount beam fitting that extends axially between a first mount beam end and a second mount beam end, and a mount beam flange that extends radially out from the mount beam fitting at the first mount beam end. A first fastener aperture extends radially through the mount beam fitting, and a second fastener aperture extends axially through the mount beam flange. The fasteners connect the mounting beam to the pylon. A first of the fasteners is mated with the first fastener aperture, and a second of the fasteners is mated with the second fastener aperture. The first mounting linkage connects the first mount beam end to a first engine attachment. The second mounting linkage connects the second mount beam end to second engine attachments.

    AXIAL TENSION SYSTEM FOR A GAS TURBINE ENGINE CASE
    6.
    发明公开
    AXIAL TENSION SYSTEM FOR A GAS TURBINE ENGINE CASE 审中-公开
    EINGEHÄUSEEINER GASTURBINE的AXIALSPANNUNGSSYSTEM

    公开(公告)号：EP2938843A4

    公开(公告)日：2016-03-23

    申请号：EP13869591

    申请日：2013-12-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： WONG JOEY ,  ZHENG ZHIJUN

    IPC: F01D25/24 ,  F01D25/00 ,  F02C7/00

    CPC classification number: F02C7/20 ,  F01D25/162 ,  F01D25/24 ,  F05D2250/711 ,  F05D2260/30

    Abstract: A gas turbine engine includes a convex case section. The convex case section includes an upstream case portion having a first radius, a downstream case portion having a second radius, and an intermediate case portion between the upstream case portion and the downstream case portion. The intermediate case portion has a third radius larger than the first radius and the second radius. A tension rod extends from the upstream case portion to the downstream case portion.

    Abstract translation: 燃气涡轮发动机包括凸壳部分。 凸形壳体部分包括具有第一半径的上游壳体部分，具有第二半径的下游壳体部分，以及在上游壳体部分和下游壳体部分之间的中间壳体部分。 中间壳体部分具有大于第一半径和第二半径的第三半径。 张力杆从上游壳体部分延伸到下游壳体部分。

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