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    GAS TURBINE ENGINE DUAL TOWERSHAFT ACCESSORY GEARBOX ASSEMBLY WITH A TRANSMISSION
    23.
    发明申请
    GAS TURBINE ENGINE DUAL TOWERSHAFT ACCESSORY GEARBOX ASSEMBLY WITH A TRANSMISSION 审中-公开

    公开(公告)号：US20180202366A1

    公开(公告)日：2018-07-19

    申请号：US15409889

    申请日：2017-01-19

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

    IPC: F02C7/32 ,  F02C7/06 ,  F02C7/36

    CPC classification number: F02C7/32 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/76 ,  F05D2240/50 ,  F05D2260/4031

    Abstract: A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, the accessory drive gearbox including a first set of gears and a second set of gears, the first towershaft extending into a housing and coupled to the first set of gears, the second towershaft extending into the housing and coupled to the second set of gears, an electric machine, and a transmission coupling the electric machine to the first set of gears, the transmission transitionable between a first mode where the electric machine is driven at a first speed relative to the first towershaft, and a second mode where the electric machine is driven at a different, second speed relative to the first towershaft.

    GAS TURBINE ENGINE SPLIT TORQUE FAN DRIVE GEAR SYSTEM
    25.
    发明申请
    GAS TURBINE ENGINE SPLIT TORQUE FAN DRIVE GEAR SYSTEM 审中-公开
    气体涡轮发动机分体转矩风扇驱动齿轮系统

    公开(公告)号：US20160208690A1

    公开(公告)日：2016-07-21

    申请号：US14597410

    申请日：2015-01-15

    Applicant: United Technologies Corporation

    Inventor： Jonathan F. Zimmitti ,  David Allen Stachowiak

    IPC: F02C3/107 ,  F02C7/36 ,  F02K3/06

    CPC classification number: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/323 ,  F05D2260/40311 ,  F16H1/22

    Abstract: A gas turbine engine includes a turbine section configured to rotate about an engine axis relative to an engine static structure. A fan section is configured to rotate about the engine axis relative to the engine static structure. A geared architecture operatively connects the fan section to the turbine section. The geared architecture includes an input gear and an output gear both configured to rotate about the engine axis. A set of idler gears are arranged radially outward relative to and operatively coupling with the input and output gears.

    Abstract translation: 燃气涡轮发动机包括涡轮部分，其构造成相对于发动机静态结构围绕发动机轴线旋转。 风扇部分被配置成围绕发动机轴线相对于发动机静态结构旋转。 齿轮架构将风扇部分可操作地连接到涡轮部分。 齿轮架构包括一个输入齿轮和一个输出齿轮，两者配置成围绕发动机轴线旋转。 一组空转齿轮相对于输入和输出齿轮径向向外布置并且可操作地联接。

    Gas Turbine Engine With Single Turbine Driving Two Compressors
    26.
    发明申请
    Gas Turbine Engine With Single Turbine Driving Two Compressors 审中-公开
    燃气轮机发动机与单涡轮驱动两台压缩机

    公开(公告)号：US20160160761A1

    公开(公告)日：2016-06-09

    申请号：US14921324

    申请日：2015-10-23

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  James D. Hill ,  William F. Schneider ,  Jonathan F. Zimmitti

    IPC: F02C7/36 ,  F02C9/16 ,  F02C3/04

    CPC classification number: F02C7/36 ,  F02C3/04 ,  F02C3/113 ,  F02C9/16 ,  F05D2220/32 ,  F05D2260/4031 ,  F05D2270/02

    Abstract: A gas turbine engine comprises a lower pressure compressor and a higher pressure compressor. A single turbine drives both the lower pressure compressor and the higher pressure compressor through a gear reduction. The gear reduction includes an actuator and at least two available speeds, such that the lower pressure compressor can selectively be operated at either of at least two speeds relative to the higher pressure compressor. A method of operating a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括低压压缩机和高压压缩机。 单个涡轮机通过齿轮减速器驱动低压压缩机和较高压力的压缩机。 齿轮减速包括致动器和至少两个可用速度，使得低压压缩机可选择性地相对于较高压力的压缩机以至少两个速度运行。 还公开了一种操作燃气涡轮发动机的方法。

    Radial seal segment joint
    27.
    发明授权
    Radial seal segment joint 有权

    公开(公告)号：US11525515B2

    公开(公告)日：2022-12-13

    申请号：US16788126

    申请日：2020-02-11

    Applicant: United Technologies Corporation

    Inventor： Jonathan F. Zimmitti ,  Nasr A. Shuaib ,  Jonathan Logan Miller

    IPC: F16J15/28 ,  F16J15/44 ,  F16J15/30

    Abstract: Apparatus and associated methods relate to a segmented radial seal assembly that includes at least two segments, each segment having a first end and a second end at opposite ends. A first segment first end has a protruding feature and defines a tangential vector from a circumferential ring that is formed by the segmented radial seal. The protruding feature defines a curved face having at least a first axis of curvature that is parallel to the tangential vector. The second segment second end has a recessed feature that is matingly engageable to the first segment first end, thereby forming a first radial seal segment joint. The segmented radial seal assembly is configured to surround a shaft.

    RADIAL SEAL SEGMENT JOINT
    29.
    发明申请
    RADIAL SEAL SEGMENT JOINT 有权

    公开(公告)号：US20210246987A1

    公开(公告)日：2021-08-12

    申请号：US16788126

    申请日：2020-02-11

    Applicant: United Technologies Corporation

    Inventor： Jonathan F. Zimmitti ,  Nasr A. Shuaib ,  Jonathan Logan Miller

    IPC: F16J15/44 ,  F16J15/28 ,  F16J15/30

    Abstract: Apparatus and associated methods relate to a segmented radial seal assembly that includes at least two segments, each segment having a first end and a second end at opposite ends. A first segment first end has a protruding feature and defines a tangential vector from a circumferential ring that is formed by the segmented radial seal. The protruding feature defines a curved face having at least a first axis of curvature that is parallel to the tangential vector. The second segment second end has a recessed feature that is matingly engageable to the first segment first end, thereby forming a first radial seal segment joint. The segmented radial seal assembly is configured to surround a shaft.

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