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    Gas turbine engine hydraulically operated nacelle latch
    21.
    发明授权
    Gas turbine engine hydraulically operated nacelle latch 有权

    公开(公告)号：US10458280B2

    公开(公告)日：2019-10-29

    申请号：US14765877

    申请日：2014-03-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Nigel David Sawyers-Abbott

    IPC: F01D25/24 ,  F01D25/28 ,  F02K1/76 ,  B64D29/06 ,  B64D29/08 ,  F02C7/20 ,  F02C7/00 ,  F02C3/04

    Abstract: A method of actuating a hydraulic latch and a fan duct includes providing a pressurized fluid for actuating a latch, providing a valve to control flow of pressurized fluid to the latch and the fan duct, and selectively opening the valve, whereby the pressurized fluid opens the fan duct. A gas turbine engine includes a fan duct with an inner structure surrounding an engine core, a fan case surrounding a fan, and at least one latch. The at least one latch secures a first portion of the fan duct inner structure to a core engine fame or to a second portion of the fan duct inner structure. The at least one latch is also configured to secure the second portion of the fan duct inner structure to the core engine fame or to the first portion of the fan duct inner structure.

    Blocker door link arm and fitting
    22.
    发明授权
    Blocker door link arm and fitting 有权

    公开(公告)号：US10294892B2

    公开(公告)日：2019-05-21

    申请号：US15131955

    申请日：2016-04-18

    Applicant: United Technologies Corporation

    Inventor： Nigel David Sawyers-Abbott ,  Priscilla Chin

    IPC: F02K1/76 ,  F01D25/24 ,  F02K1/62 ,  F02K1/72 ,  F02K1/80

    Abstract: Systems for thrust reverser link arm connections are described herein. A fitting for a thrust reverser link arm may comprise a base plate configured to be fastened to a proximal surface of an inner fixed structure (IFS), a first wall extending orthogonally from the base plate, a pin extending orthogonally from the first wall, a second wall extending orthogonally from the base plate, a removable member, a first column located between the first wall and the second wall, and a second column located between the first wall and the second wall. The removable member may surround at least a portion of the pin. The removable member may be removed from a radially outward side of the IFS.

    INLET COWL DEFLECTION LIMITING STRUT
    23.
    发明申请
    INLET COWL DEFLECTION LIMITING STRUT 审中-公开

    公开(公告)号：US20190055026A1

    公开(公告)日：2019-02-21

    申请号：US15681987

    申请日：2017-08-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Nigel David Sawyers-Abbott ,  Frederick M. Schwarz

    IPC: B64D27/26 ,  F02C7/20 ,  F01D25/28

    Abstract: A turbofan engine may comprise an inlet and a fan case coupled to the inlet. An engine case may be coupled to the fan case via a vane extending between the fan case and the engine case. A strut apparatus may extend from the fan case and limit deflection of the fan case. The strut apparatus may comprise a first end proximate the fan case, and a second end coupled to at least one of the engine case or a structure for mounting the turbofan engine to an aircraft.

    COMBINED INLET LAMINAR AND THRUST REVERSER CASCADE EFFLUX FLOW CONTROL SYSTEM
    27.
    发明申请
    COMBINED INLET LAMINAR AND THRUST REVERSER CASCADE EFFLUX FLOW CONTROL SYSTEM 有权
    组合式入口板和扭矩反向器CASCADE EFFLUX流量控制系统

    公开(公告)号：US20160298574A1

    公开(公告)日：2016-10-13

    申请号：US14684503

    申请日：2015-04-13

    Applicant: United Technologies Corporation

    Inventor： Nigel David Sawyers-Abbott

    IPC: F02K1/54 ,  B64D27/10 ,  F02C3/04 ,  B64D29/00

    CPC classification number: F02K1/54 ,  B64C21/04 ,  B64C21/06 ,  B64C21/08 ,  B64D27/10 ,  B64D29/00 ,  B64D2033/0226 ,  F02C3/04 ,  F02K1/72 ,  F02K1/76 ,  F02K3/06 ,  F05D2210/34 ,  F05D2270/17

    Abstract: A nacelle assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan nacelle bounding a bypass flow path. The fan nacelle includes a first nacelle section and a second nacelle section. The second nacelle section includes a moveable portion movable relative to a forward portion to define a secondary flow passage. The first nacelle section includes an inlet lip. A thrust reverser is configured to selectively communicate a portion of bypass airflow between the bypass flow path and the secondary flow passage. A pump is configured to selectively communicate airflow between the inlet lip and the secondary flow passage. A method of flow distribution for a gas turbine engine is also disclosed.

    Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的机舱组件尤其包括限定旁路流动路径的风扇机舱。 风扇机舱包括第一机舱部分和第二机舱部分。 第二机舱部分包括可相对于前部移动以限定次流通道的可移动部分。 第一机舱部分包括入口唇缘。 推力反向器构造成选择性地将旁路气流的一部分在旁路流动路径和次流通道之间进行通信。 泵构造成选择性地在入口唇缘和次流道之间连通气流。 还公开了一种用于燃气涡轮发动机的流量分配的方法。

    CASTELLATED LATCH MECHANISM FOR A GAS TURBINE ENGINE
    29.
    发明申请
    CASTELLATED LATCH MECHANISM FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的机舱锁紧机构

    公开(公告)号：US20160032779A1

    公开(公告)日：2016-02-04

    申请号：US14774168

    申请日：2014-03-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Nigel David Sawyers-Abbott

    IPC: F01D25/26 ,  F01D15/10 ,  F02C3/04

    CPC classification number: F01D25/265 ,  B64D29/06 ,  B64D29/08 ,  F01D15/10 ,  F01D25/246 ,  F01D25/28 ,  F02C3/04 ,  F02C7/20 ,  F02K1/72 ,  F02K1/80 ,  F02K1/805 ,  F05D2220/32 ,  F05D2250/182 ,  F05D2250/71 ,  F05D2260/36

    Abstract: A gas turbine engine includes a fan duct including a fan duct inner structure that surrounds a core engine, a fan case that surrounds a fan, a core engine frame, and at least one mechanism configured to secure a portion of the fan duct inner structure to a portion of the core engine frame. The at least one mechanism includes a castellated arcuate portion mounted to one of the fan duct inner structure and the core engine frame and an inwardly projecting retaining feature mounted to the other of the fan duct inner structure and the core engine frame. The castellated arcuate portion is rotatable about an engine central longitudinal axis to position a feature of the castellated arcuate portion proximate to a portion of the inwardly projecting retaining feature to latch the fan duct inner structure.

    Abstract translation: 燃气涡轮发动机包括风扇管道，风扇管道包括围绕发动机的风扇管道内部结构，围绕风扇的风扇壳体，核心发动机框架，以及至少一个机构，其构造成将风扇管道内部结构的一部分固定到 核心引擎框架的一部分。 所述至少一个机构包括安装到所述风扇管道内部结构和所述核心发动机框架中的一个的雉形弧形部分，以及安装到所述风扇管道内部结构和所述核心引擎框架中的另一个的向内突出的保持特征。 雉形弧形部分可围绕发动机中心纵向轴线旋转，以将cast形弧形部分的特征定位成靠近向内突出的保持特征的一部分，以锁住风扇管道内部结构。

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