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    FLASH THERMOGRAPHY DOUBLE WALL THICKNESS MEASUREMENT
    2.
    发明公开
    FLASH THERMOGRAPHY DOUBLE WALL THICKNESS MEASUREMENT 有权
    带双壁厚FLASH热计量

    公开(公告)号：EP2962061A1

    公开(公告)日：2016-01-06

    申请号：EP14757641.7

    申请日：2014-02-27

    申请人： United Technologies Corporation

    发明人： OUYANG, Zhong ,  RAULERSON, David A. ,  SMITH, Kevin D. ,  PINERO, Hector M. ,  TARASKEVICH, Jaimie ,  BOYER, Jesse R.

    IPC分类号： G01B11/06

    CPC分类号： G01B21/085 ,  G01J5/0088 ,  G01J5/0896 ,  G01J2005/0081 ,  G01N25/00

    摘要： A method of determining the thickness of an internal wall in a gas turbine engine component includes the steps of utilizing flash thermography to measure a complete thickness of a component between an outer wall and at least one enlarged cooling channel at a location where an outer cooling channel is positioned between the outer wall and the at least one enlarged cooling channel and where at least one member spans the cooling channel, such that the thickness is through the member which spans the outer cooling channel. An outer thickness of the component is measured from the outer wall to an outer wall of the outer cooling channel. A thickness is determined from an inner wall of the outer cooling channel to the at least one enlarged cooling channel by subtracting the measured outer thickness from the complete thickness, and also subtracting a known thickness of the outer cooling channel.

    HIGH PRESSURE TURBINE COOLANT SUPPLY SYSTEM
    4.
    发明公开
    HIGH PRESSURE TURBINE COOLANT SUPPLY SYSTEM 审中-公开
    冷却液供给系统高压涡轮

    公开(公告)号：EP2855884A1

    公开(公告)日：2015-04-08

    申请号：EP13797827.6

    申请日：2013-05-15

    申请人： United Technologies Corporation

    发明人： MOSLEY, John H. ,  ALVANOS, Ioannis ,  STRIPINIS, Philip S. ,  FREIBERG, Douglas Paul ,  PINERO, Hector M. ,  O'CONNOR, John J. ,  PIETROBON, Jon

    IPC分类号： F02C7/12 ,  F01D25/08

    CPC分类号： F01D5/082 ,  F01D25/12

    摘要： A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.