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    4.
    发明专利
    未知

    公开(公告)号：AT496212T

    公开(公告)日：2011-02-15

    申请号：AT04252606

    申请日：2004-05-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SYNDER TIMOTHY S ,  BUEY JOHN R ,  BRDAR CHRISTOPHER R

    IPC: F02K3/00 ,  F02K3/11 ,  F02K3/10 ,  F23D11/12 ,  F23D11/38 ,  F23R3/20 ,  F23R3/28

    Abstract: A gas turbine engine augmentor (72) nozzle has an inlet (104) for connection to an augmentor fuel conduit and an outlet (106) for expelling a spray of fuel. A passageway (110) between the inlet (104) and outlet (106) is at least partially bounded by outlet end surface portions (126,128) diverging from each other. The nozzle (70) may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline (150) toward radial.

    6.
    发明专利
    未知

    公开(公告)号：NO20041951L

    公开(公告)日：2004-11-15

    申请号：NO20041951

    申请日：2004-05-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BUEY JOHN R ,  SNYDER TIMOTHY S ,  BRDAR CHRISTOPHER R

    IPC: F02K3/00 ,  F02K3/10 ,  F23D11/12 ,  F23R3/20 ,  F23R3/28 ,  F02K1/10 ,  F02K1/00 ,  F02K1/30

    Abstract: A gas turbine engine augmentor (72) nozzle has an inlet (104) for connection to an augmentor fuel conduit and an outlet (106) for expelling a spray of fuel. A passageway (110) between the inlet (104) and outlet (106) is at least partially bounded by outlet end surface portions (126,128) diverging from each other. The nozzle (70) may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline (150) toward radial.

    COATED COOLING PASSAGE
    10.
    发明公开
    COATED COOLING PASSAGE 审中-公开
    涂层冷却通道

    公开(公告)号：EP3066322A4

    公开(公告)日：2016-11-30

    申请号：EP14857449

    申请日：2014-09-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BURD STEVEN W ,  BRDAR CHRISTOPHER R ,  PHILIPPONA DERK S

    IPC: F02C7/24 ,  F01D25/12 ,  F01D25/30 ,  F02C7/12 ,  F02K1/82

    CPC classification number: F01D25/305 ,  F01D25/145 ,  F01D25/30 ,  F02C7/12 ,  F02K1/822 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/15 ,  F05D2250/38 ,  F05D2260/202 ,  F05D2260/231 ,  Y02T50/675

    Abstract: A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.

    Abstract translation: 用于燃气涡轮发动机的部件包括具有基板开口的基板和在基板上延伸一定长度的基板孔的涂层。 用于燃气涡轮发动机的衬套组件包括具有多个孔的热片和在热片上的涂层，其延伸多个孔的每一个的长度。 形成用于在燃气涡轮发动机的部件中提供薄膜冷却的孔的方法包括在基板中形成多个基板孔。 多个基板孔中的每一个限定基板内周边。 在形成多个基板孔之后，在基板上施加涂层以至少部分地在多个基板孔内的每一个内限定涂层内周边。 涂层内周面小于基板内周。

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