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    COOLANT FLOW REDIRECTION COMPONENT
    4.
    发明申请
    COOLANT FLOW REDIRECTION COMPONENT 审中-公开

    公开(公告)号：US20180094528A1

    公开(公告)日：2018-04-05

    申请号：US15800544

    申请日：2017-11-01

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey ,  Elizabeth F. Vinson

    IPC: F01D5/18 ,  F04D29/32 ,  F04D29/58 ,  F04D29/053 ,  F02C3/04 ,  F01D5/08

    Abstract: A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor and mechanically connected to the compressor section via a shaft. Multiple rotors are disposed in one of the compressor section and the turbine section. Each of the rotors includes a rotor disk portion having a radially inward bore, and is static relative to the shaft. Each rotor is axially adjacent at least one other rotor and a gap is defined between each rotor and an adjacent rotor. A cooling passage for a cooling flow is defined between the shaft and the rotors, and a cooling flow redirection component is disposed at the gap and is operable to redirect the cooling flow in the cooling passage into the gap.

    AIRFOIL RESONANT FREQUENCY TESTING
    5.
    发明申请
    AIRFOIL RESONANT FREQUENCY TESTING 有权
    飞机谐振频率测试

    公开(公告)号：US20160230588A1

    公开(公告)日：2016-08-11

    申请号：US14619757

    申请日：2015-02-11

    Applicant: United Technologies Corporation

    Inventor： Steven Tine ,  Richard A. Lomenzo,, JR. ,  Kevin J. Klinefelter ,  Elizabeth F. Vinson ,  Kaitlin Olsen ,  Thomas R. Davis

    IPC: F01D21/00 ,  G01H9/00 ,  G01H13/00

    CPC classification number: F01D21/003 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/12 ,  G01H9/00 ,  G01H13/00

    Abstract: A resonant frequency testing system for airfoils comprises a broach block, a clamp, an acoustic speaker, a laser vibrometer, and a control processor assembly. The broach block has a slot disposed to receive the airfoil in an airfoil location. The clamp has a torque-actuated shutoff, and is disposed to lock the airfoil in the broach block slot under a fixed clamping force. The acoustic sensor is disposed adjacent the airfoil location to emit sonic pulses, and the laser vibrometer is oriented towards the airfoil location to sense vibration signatures of the airfoil when excited by the sonic pulses. The control processor assembly is configured to control the acoustic speaker and laser vibrometer, to decompose the sensed vibration signatures into resonant frequencies of the airfoil, and to store the resonant frequencies in a digital storage database, correlated with a unique ID corresponding to the airfoil

    Abstract translation: 用于翼型件的谐振频率测试系统包括拉锯块，夹具，声音扬声器，激光振动计和控制处理器组件。 拉刀块具有设置成在翼型位置接收翼型的槽。 夹具具有扭矩驱动关闭，并且被设置成在固定夹紧力下将翼型件锁定在拉刀块槽中。 声学传感器设置在翼型位置附近以发射声波脉冲，并且激光振动计朝向翼型位置定向以在由声波脉冲激发时感测到翼型的振动特征。 控制处理器组件被配置为控制声学扬声器和激光振动计，将感测到的振动特征分解成翼型的谐振频率，并将共振频率存储在数字存储数据库中，与对应于翼型的唯一ID相关联

    SEAL RING
    7.
    发明申请
    SEAL RING 审中-公开

    公开(公告)号：US20200025293A1

    公开(公告)日：2020-01-23

    申请号：US16243632

    申请日：2019-01-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John J. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  John E. Paul ,  Ross Wilson ,  Edwin Otero ,  Alan W. Stoner

    IPC: F16J15/44 ,  F01D11/02

    Abstract: A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.

    Airfoil retention assembly for a gas turbine engine
    9.
    发明授权
    Airfoil retention assembly for a gas turbine engine 有权

    公开(公告)号：US10415401B2

    公开(公告)日：2019-09-17

    申请号：US15259641

    申请日：2016-09-08

    Applicant: United Technologies Corporation

    Inventor： Noah Wadsworth ,  Elizabeth F. Vinson

    IPC: F01D5/30 ,  F01D5/06 ,  F01D5/12 ,  F04D19/02 ,  F04D25/04 ,  F01D5/32

    Abstract: An airfoil retention assembly for a gas turbine engine includes, among other things, a disk, a coverplate, and a retaining ring. The disk defines a disk axis and an array of slots for receiving airfoil blades. The coverplate is dimensioned to radially overlap the array of slots relative to the disk axis. The retaining ring includes a ring body extending circumferentially about the disk axis between first and second ring ends to define a ring length. First and second retaining features continue along first and second circumferential faces of the ring body, respectively, to define first and second lengths, respectively. At least one of the first and second lengths is less than the ring length.

    Airfoil resonant frequency testing
    10.
    发明授权
    Airfoil resonant frequency testing 有权

    公开(公告)号：US09777591B2

    公开(公告)日：2017-10-03

    申请号：US14619757

    申请日：2015-02-11

    Applicant: United Technologies Corporation

    Inventor： Steven Tine ,  Richard A. Lomenzo, Jr. ,  Kevin J. Klinefelter ,  Elizabeth F. Vinson ,  Kaitlin Olsen ,  Thomas R. Davis

    IPC: G01H13/00 ,  G01H9/00 ,  F01D21/00

    CPC classification number: F01D21/003 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/12 ,  G01H9/00 ,  G01H13/00

    Abstract: A resonant frequency testing system for airfoils comprises a broach block, a clamp, an acoustic speaker, a laser vibrometer, and a control processor assembly. The broach block has a slot disposed to receive the airfoil in an airfoil location. The clamp has a torque-actuated shutoff, and is disposed to lock the airfoil in the broach block slot under a fixed clamping force. The acoustic sensor is disposed adjacent the airfoil location to emit sonic pulses, and the laser vibrometer is oriented towards the airfoil location to sense vibration signatures of the airfoil when excited by the sonic pulses. The control processor assembly is configured to control the acoustic speaker and laser vibrometer, to decompose the sensed vibration signatures into resonant frequencies of the airfoil, and to store the resonant frequencies in a digital storage database, correlated with a unique ID corresponding to the airfoil.

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