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    GAS TURBINE ENGINE SPOOL COUPLING
    1.
    发明申请
    GAS TURBINE ENGINE SPOOL COUPLING 有权

    公开(公告)号：US20210040896A1

    公开(公告)日：2021-02-11

    申请号：US16536526

    申请日：2019-08-09

    申请人： United Technologies Corporation

    发明人： Matthew R. Feulner ,  Gary Collopy

    IPC分类号： F02C9/00 ,  F01D25/34

    摘要： A system includes a gas turbine engine having a low speed spool and a high speed spool. The system also includes a spool coupling system configured to mechanically link the low speed spool and the high speed spool. A controller is operable to determine a mode of operation of the gas turbine engine, monitor for a spool coupling activation condition associated with the mode of operation, and activate the spool coupling system based on the controller detecting the spool coupling activation condition. Engagement and power transfer between the low speed spool and the high speed spool occurs based on activation of the spool coupling system and reaching an engagement condition of the spool coupling system.

    TURBOCOMPRESSOR FOR AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM
    3.
    发明申请
    TURBOCOMPRESSOR FOR AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM 审中-公开

    公开(公告)号：US20170241340A1

    公开(公告)日：2017-08-24

    申请号：US15047947

    申请日：2016-02-19

    申请人： United Technologies Corporation

    发明人： Matthew R. Feulner

    IPC分类号： F02C6/08 ,  B64D13/06 ,  B64D15/04 ,  F02C3/04 ,  F02C9/18

    摘要： A bleed air system for an aircraft includes a turbocompressor including a turbine portion coupled to drive a compressor portion. The compressor portion includes a compressor inlet and a compressor air discharge. The turbine portion includes a turbine inlet and a turbine discharge. A passage delivers air to the compressor inlet from one or more locations of an engine. A passage delivers air to the turbine inlet from at least one or more locations of the engine. A passage receives air from the compressor discharge selectively delivered to one or more locations of the engine. An outlet passage receives air from the turbine discharge communicating airflow to an aircraft system. A controller directs inlet and discharge airflow of the compressor portion and the turbine portion to control operation of the turbocompressor. A gas turbine engine and a method are also disclosed.

    MODEL BASED FUEL-AIR RATIO CONTROL
    4.
    发明申请
    MODEL BASED FUEL-AIR RATIO CONTROL 审中-公开
    基于模型的燃油比控制

    公开(公告)号：US20140090392A1

    公开(公告)日：2014-04-03

    申请号：US13631394

    申请日：2012-09-28

    申请人： United Technologies Corporation

    发明人： Richard P. Meisner ,  Brian V. Winebrenner ,  Matthew R. Feulner ,  Boris Karpman ,  David L. Ma

    IPC分类号： F02C9/54

    CPC分类号： F02C9/54 ,  F02C9/26 ,  F05D2270/092 ,  F05D2270/71 ,  F23N2023/40 ,  F23N2041/20 ,  Y02T50/677

    摘要： A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to estimate combustor fuel-air ratio based on a realtime model-based estimate of combustor airflow, and commands engine actuators to correct for a difference between the estimated combustor fuel-air ratio and a limit fuel-air ratio selected to avoid lean blowout.

    摘要翻译： 燃气涡轮发动机包括压缩机，燃烧器，涡轮机和电子发动机控制系统。 压缩机，燃烧器和涡轮机以流动系列布置。 电子发动机控制系统被配置为基于燃烧器空气流的基于实时模型的估计来估计燃烧器燃料空气比，并且命令发动机执行器来校正估计的燃烧器燃料空气比和极限燃料空气比之间的差 选择避免精益井喷。

    ACTIVE MULTI-EFFECTOR CONTROL OF HIGH PRESSURE TURBINE CLEARANCES
    5.
    发明申请
    ACTIVE MULTI-EFFECTOR CONTROL OF HIGH PRESSURE TURBINE CLEARANCES 审中-公开

    公开(公告)号：US20200332726A1

    公开(公告)日：2020-10-22

    申请号：US16388227

    申请日：2019-04-18

    申请人： United Technologies Corporation

    发明人： Joseph Kehoe ,  Richard P. Meisner ,  Manuj Dhingra ,  Patrick D. Couture ,  Matthew R. Feulner ,  Brenda J. Lisitano ,  Christopher L. Ho

    IPC分类号： F02C9/54

    摘要： A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.

    Engine Inlet Total Air Temperature Sensor
    10.
    发明申请
    Engine Inlet Total Air Temperature Sensor 审中-公开
    发动机进气口总气温传感器

    公开(公告)号：US20160032757A1

    公开(公告)日：2016-02-04

    申请号：US14774519

    申请日：2013-12-16

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Xuejun Liu ,  Matthew R. Feulner

    IPC分类号： F01D17/08 ,  F01D21/00

    CPC分类号： F01D17/085 ,  B64D33/00 ,  F01D21/003 ,  F05D2260/80 ,  G01K13/02 ,  G01K13/028 ,  G01K2013/024 ,  G01K2205/02

    摘要： A total air temperature (TAT) sensor assembly is disclosed. The assembly includes a housing that accommodates a temperature sensor. The assembly also includes a first airfoil that includes a leading end and a trailing end and a second airfoil that includes a leading end and a trailing end. The first and second airfoils are disposed in a spaced-apart fashion that defines a curved passageway so incoming air can flow between the first and second airfoils before engaging the housing and the temperature sensor. The trailing ends of the airfoils are disposed on opposite sides of the housing and spaced apart from the housing to permit air flowing through the curved passageway to pass the housing.

    摘要翻译： 公开了一种总空气温度（TAT）传感器组件。 组件包括容纳温度传感器的壳体。 组件还包括包括前端和后端的第一翼型件和包括前端和后端的第二翼型件。 第一和第二翼型件以间隔开的方式设置，其限定弯曲的通道，使得在接合外壳和温度传感器之前，进入的空气可以在第一和第二翼型之间流动。 翼型件的后端设置在壳体的相对侧并且与壳体间隔开，以允许空气流过弯曲通道以使壳体通过。