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    GAS TURBINE ENGINE WITH EMBEDDED DISTRIBUTED FANS
    11.
    发明申请
    GAS TURBINE ENGINE WITH EMBEDDED DISTRIBUTED FANS 审中-公开
    具有嵌入式分布式风机的气体涡轮发动机

    公开(公告)号：US20150361879A1

    公开(公告)日：2015-12-17

    申请号：US14600304

    申请日：2015-01-20

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Jesse M. Chandler ,  Stephen G. Pixton

    IPC: F02C3/10 ,  B64D33/02 ,  B64D33/04 ,  F02K1/54 ,  B64D27/12

    CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C6/206 ,  F02C7/36 ,  F02K1/54

    Abstract: An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed.

    Abstract translation: 飞机主体包括支撑结构。 燃气涡轮发动机包括具有至少一个压缩机转子，至少一个气体发生器涡轮机转子和燃烧部分的气体发生器。 风扇驱动涡轮机位于至少一个气体发生器涡轮转子的下游，并且构造成驱动轴。 轴接合齿轮以驱动多个风扇转子。 燃气涡轮发动机被嵌入到支撑结构中，使得有一个入口通过支撑结构通向风扇转子，以将空气输送到风扇转子。 还公开了一种燃气涡轮发动机。

    VIRTUAL MULTI-STREAM GAS TURBINE ENGINE
    12.
    发明申请
    VIRTUAL MULTI-STREAM GAS TURBINE ENGINE 有权
    虚拟多流量涡轮发动机

    公开(公告)号：US20150361819A1

    公开(公告)日：2015-12-17

    申请号：US14604228

    申请日：2015-01-23

    Applicant: United Technologies Corporation

    Inventor： Alan H. Epstein

    IPC: F01D17/12 ,  F01D9/04 ,  F01D25/24 ,  F01D5/02

    CPC classification number: F01D9/041 ,  F01D1/023 ,  F01D5/148 ,  F01D5/225 ,  F01D17/162 ,  F02C9/20 ,  F02K3/075 ,  F02K3/077 ,  F04D29/563 ,  Y02T50/673

    Abstract: A gas turbine engine is provided that includes a core flow path to direct a core stream flow. A common flow path is outboard of the core flow path, where the common flow path directs both a second stream flow and a third stream flow. Another gas turbine engine is provided that includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is inboard of the outer case structure, where the intermediate case structure and the outer case structure direct both a third stream flow and a second stream flow. An inner case structure is inboard of the intermediate case structure, where the inner case structure and the intermediate case structure direct a core stream flow.

    Abstract translation: 提供了一种燃气涡轮发动机，其包括用于引导芯流流动的芯流动路径。 公共流动路径在核心流动路径的外侧，其中公共流动路径引导第二流和第三流。 提供另一燃气涡轮发动机，其包括围绕中心纵向发动机轴线的外壳结构。 中间壳结构在外壳结构的内侧，其中中间壳结构和外壳结构指向第三流流和第二流流。 内壳结构在中间壳结构的内侧，其中内壳结构和中间壳结构引导芯流流。

    Electric rotor dynamics damping
    13.
    发明授权
    Electric rotor dynamics damping 有权

    公开(公告)号：US11378061B2

    公开(公告)日：2022-07-05

    申请号：US15986980

    申请日：2018-05-23

    Applicant: United Technologies Corporation

    Inventor： Alan H. Epstein

    IPC: G05B5/01 ,  F03D7/02 ,  F03D17/00 ,  F03D7/04

    Abstract: A rotor dynamics adjustment system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The rotor dynamics adjustment system also includes one or more rotor system sensors configured to collect a plurality of sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to monitor the one or more rotor system sensors while the rotor system is rotating. A dynamic motion of the rotor system is characterized based on the sensor data from the one or more rotor system sensors. A damping correction torque is determined to diminish the dynamic motion of the rotor system. The electric motor is commanded to apply the damping correction torque to the rotor system.

    Cooled Information Node
    16.
    发明申请
    Cooled Information Node 审中-公开
    冷却信息节点

    公开(公告)号：US20170058693A1

    公开(公告)日：2017-03-02

    申请号：US14853449

    申请日：2015-09-14

    Applicant: United Technologies Corporation

    Inventor： Alan H. Epstein

    IPC: F01D21/00 ,  H04L29/08

    CPC classification number: H04L67/12 ,  F02C7/00 ,  F02C7/12 ,  F05D2260/20 ,  F05D2270/54 ,  Y02T50/671 ,  Y02T50/675

    Abstract: An information node is presented for use within a thermally challenged environment. The cooled information node has a case with a thermoelectric conditioner. A thermoelectric controller contained within the case operates the thermoelectric conditioner. A transceiver/power conditioner connects to both the thermoelectric controller and a processor and is configured to receive and transmit data signals from an outside source. The cooled information node also has a signal input/output module connected to each the transceiver/power conditioner, the processor and the thermoelectric controller. The signal input/output module is configured to receive and transmit another data signal from another outside source. The information node may be used within an electronic network connecting multiple outside sources to a central source. Furthermore, the information node may be used within a gas turbine engine for communication between engine components and the electronic engine control of the gas turbine engine.

    Abstract translation: 提供了一个信息节点，用于受热攻击的环境中。 冷却的信息节点具有热电调节器的情况。 包含在壳体内的热电控制器操作热电调节器。 收发器/功率调节器连接到热电控制器和处理器，并且被配置为从外部源接收和发送数据信号。 冷却的信息节点还具有连接到每个收发器/功率调节器，处理器和热电控制器的信号输入/输出模块。 信号输入/输出模块被配置为从另一个外部源接收和发送另一个数据信号。 信息节点可以在将多个外部源连接到中央源的电子网络内使用。 此外，信息节点可以在燃气涡轮发动机内用于发动机部件与燃气涡轮发动机的电子发动机控制之间的通信。

    AIRCRAFT ENGINE IDLE SUPPRESSOR AND METHOD
    19.
    发明申请
    AIRCRAFT ENGINE IDLE SUPPRESSOR AND METHOD 审中-公开

    公开(公告)号：US20200056551A1

    公开(公告)日：2020-02-20

    申请号：US16105642

    申请日：2018-08-20

    Applicant: United Technologies Corporation

    Inventor： Alan H. Epstein

    IPC: F02C9/48 ,  F02C3/04 ,  F04D27/00 ,  F02C7/268 ,  B64D27/02

    Abstract: An embodiment of an engine assembly includes a combustion turbine engine having at least a first compressor spool, a first turbine spool, a first shaft connecting the first compressor spool and the first turbine spool, and a combustor disposed in a working gas flow path between the first compressor spool and the first turbine spool. A first controller is programmed with a surge map, and configured to operate the combustion turbine engine in a range extending between a first suppressed idle mode, a second base idle mode, and a maximum takeoff power rating mode. An idle speed suppressor includes at least one idle assist motor connected to the first shaft of the combustion turbine engine. A second controller is configured to manage operation of the idle speed suppressor relative to the combustion turbine engine during times of minimum power demand, such that operating the idle speed suppressor increases a compressor speed in the first suppressed idle mode relative to a compressor speed in the second base idle mode.

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