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    GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR AND THERMAL MANAGEMENT
    2.
    发明申请
    GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR AND THERMAL MANAGEMENT 审中-公开
    具有入口颗粒分离器和热管理的气体涡轮发动机

    公开(公告)号：WO2014078003A2

    公开(公告)日：2014-05-22

    申请号：PCT/US2013/065337

    申请日：2013-10-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  EPSTEIN, Alan H. ,  LORD, Wesley K. ,  CHANDLER, Jesse M.

    IPC: F02C7/052 ,  F02C7/12

    CPC classification number: F01D25/08 ,  F02C7/052 ,  Y02T50/675

    Abstract: A gas turbine engine includes a nose cone at an inlet end, and spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. Air delivered by the inlet particle separator passes over a heat exchanger before passing to an outlet.

    Abstract translation: 燃气涡轮发动机包括在入口端处的鼻锥体，并且在机舱的径向内侧间隔开。 压缩机在鼻锥的下游。 核心入口将鼻锥下游的空气输送到压缩机中。 入口颗粒分离器包括用于沿芯入口径向向外输送空气的歧管。 通过入口颗粒分离器输送的空气在通过出口之前通过热交换器。

    GAS TURBINE ENGINE SYSTEM COOLDOWN
    5.
    发明公开
    GAS TURBINE ENGINE SYSTEM COOLDOWN 审中-公开

    公开(公告)号：EP3628820A2

    公开(公告)日：2020-04-01

    申请号：EP19199806.1

    申请日：2019-09-26

    Applicant: United Technologies Corporation

    Inventor： EPSTEIN, Alan H.

    IPC: F01D9/02 ,  F01D21/00 ,  F01D25/34

    Abstract: An engine system for an aircraft (100) includes a first gas turbine engine (20A), a first core turning system (202A), a second gas turbine engine (20B), and a second core turning system (202B). The engine system also includes a controller (214) operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.

    AIRCAFT ENGINE IDLE SUPPRESSOR AND METHOD
    6.
    发明公开
    AIRCAFT ENGINE IDLE SUPPRESSOR AND METHOD 审中-公开

    公开(公告)号：EP3613970A1

    公开(公告)日：2020-02-26

    申请号：EP19191132.0

    申请日：2019-08-09

    Applicant: United Technologies Corporation

    Inventor： EPSTEIN, Alan H.

    IPC: F02C7/275 ,  F02C9/00

    Abstract: An embodiment of an engine assembly includes a combustion turbine engine (10; 110) having at least a first compressor spool, a first turbine spool, a first shaft (44; 144) connecting the first compressor spool and the first turbine spool, and a combustor (16; 116) disposed in a working gas flow path between the first compressor spool and the first turbine spool. A first controller (46; 146) is programmed with a surge map, and configured to operate the combustion turbine engine (10; 110) 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 (36) includes at least one idle assist motor (48) connected to the first shaft (44; 144) of the combustion turbine engine (10; 110). A second controller (52; 152) is configured to manage operation of the idle speed suppressor (36) relative to the combustion turbine engine (10; 110) during times of minimum power demand, such that operating the idle speed suppressor (36) increases a compressor speed in the first suppressed idle mode relative to a compressor speed in the second base idle mode.

    COOLED INFORMATION NODE
    7.
    发明公开
    COOLED INFORMATION NODE 审中-公开
    GEKÜHLTERINFORMATIONSKNOTEN

    公开(公告)号：EP3139019A1

    公开(公告)日：2017-03-08

    申请号：EP16186710.6

    申请日：2016-08-31

    Applicant: United Technologies Corporation

    Inventor： EPSTEIN, Alan H.

    IPC: F02C7/18 ,  H05K7/20

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

    Abstract: An information node (100) is presented for use within a thermally challenged environment. The cooled information node has a case (110) with a thermoelectric conditioner (120). A thermoelectric controller (190) contained within the case operates the thermoelectric conditioner (120). A transceiver/power conditioner (160) connects to both the thermoelectric controller (190) and a processor (180) and is configured to receive and transmit data signals from an outside source (65). The cooled information node (100) also has a signal input/output module connected to each of the transceiver/power conditioner (160), the processor (180) and the thermoelectric controller (190). The signal input/output module is configured to receive and transmit another data signal from another outside source (80). The information node (100) may be used within an electronic network connecting multiple outside sources (100) to a central source (65). Furthermore, the information node (100) may be used within a gas turbine engine (20) for communication between engine components (80) and the electronic engine control (65) of the gas turbine engine.

    Abstract translation: 呈现信息节点（100）以在受热攻击的环境中使用。 冷却的信息节点具有热电调节器（120）的壳体（110）。 容纳在壳体内的热电控制器（190）操作热电调节器（120）。 收发器/功率调节器（160）连接到热电控制器（190）和处理器（180），并且被配置为从外部源（65）接收和发送数据信号。 冷却的信息节点（100）还具有连接到每个收发器/功率调节器（160），处理器（180）和热电控制器（190）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（80）接收和发送另一个数据信号。 信息节点（100）可以在将多个外部源（100）连接到中央源（65）的电子网络内使用。 此外，信息节点（100）可以用在燃气涡轮发动机（20）内，用于在发动机部件（80）和燃气涡轮发动机的电子发动机控制（65）之间进行通信。

    GAS TURBINE ENGINE SYSTEM COOLDOWN
    8.
    发明公开
    GAS TURBINE ENGINE SYSTEM COOLDOWN 审中-公开

    公开(公告)号：EP3628820A3

    公开(公告)日：2020-06-03

    申请号：EP19199806.1

    申请日：2019-09-26

    Applicant: United Technologies Corporation

    Inventor： EPSTEIN, Alan H.

    IPC: F01D9/02 ,  F01D21/00 ,  F01D25/34

    Abstract: An engine system for an aircraft (100) includes a first gas turbine engine (20A), a first core turning system (202A), a second gas turbine engine (20B), and a second core turning system (202B). The engine system also includes a controller (214) operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.

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