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    AIRFOIL COOLING PASSAGE
    2.
    发明申请
    AIRFOIL COOLING PASSAGE 审中-公开
    AIRFOIL冷却通道

    公开(公告)号：US20160326894A1

    公开(公告)日：2016-11-10

    申请号：US14706518

    申请日：2015-05-07

    Applicant: United Technologies Corporation

    Inventor： Mark A. Boeke ,  Jeffrey J. DeGray ,  Richard M. Salzillo

    IPC: F01D9/04 ,  F01D25/12

    CPC classification number: F01D9/041 ,  F01D25/12 ,  F05D2240/81 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes a first platform located at a first end of a first airfoil. A cooling passage extends through the first platform and includes a first portion that has a first thickness and a second portion that has a second thickness and surrounds opposing ends of the first portion.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括位于第一翼型件的第一端的第一平台。 冷却通道延伸穿过第一平台并且包括具有第一厚度的第一部分和具有第二厚度并且包围第一部分的相对端部的第二部分。

    Airfoil with variable trip strip height
    6.
    发明授权
    Airfoil with variable trip strip height 有权
    具有可变跳闸带高度的翼型

    公开(公告)号：US09334755B2

    公开(公告)日：2016-05-10

    申请号：US13630107

    申请日：2012-09-28

    Applicant: United Technologies Corporation

    Inventor： Sarah Riley ,  Mark A. Boeke ,  Jeffrey J. DeGray ,  Shawn J. Gregg

    IPC: F01D5/18 ,  F01D25/12 ,  F01D9/02

    CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D9/02 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2250/183 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/672 ,  Y02T50/676

    Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 一个V形形状的跳闸条从一个长度的跳闸带高度从表面延伸到冷却通道中。 跳闸条高度沿长度变化。 用于燃气涡轮发动机的涡轮叶片包括内平台和外平台。 在内平台上设有冷却通道。 冷却通道由第一和第二径向延伸的腿部彼此周向间隔开并且通过周向通道彼此连接而设置。 一对翼型件从相同的内平台径向延伸。 跳闸条沿着一段长度以一个跳闸带高度从表面延伸到圆周通道中。 行程长度沿长度变化。

    VANE INTERSEGMENT GAP SEALING ARRANGEMENT
    8.
    发明申请
    VANE INTERSEGMENT GAP SEALING ARRANGEMENT 审中-公开

    公开(公告)号：US20180106158A1

    公开(公告)日：2018-04-19

    申请号：US15295694

    申请日：2016-10-17

    Applicant: United Technologies Corporation

    Inventor： Mark A. Boeke ,  Jeffrey J. DeGray ,  Richard M. Salzillo, JR.

    IPC: F01D11/00 ,  F01D9/04

    Abstract: A stator vane rail is provided. The stator vane rail may comprise a forward rail, an aft rail located axially opposite the forward rail, a first axial surface extending between the forward rail and the aft rail, a first feather seal slot disposed in the first axial surface, wherein a terminus of the first feather seal slot is radially spaced from a radial surface of the aft rail, a second axial surface extending between the forward rail and the aft rail, and a second feather seal slot disposed in the second axial surface, wherein the second feather seal slot extends from the radial surface of the aft rail.

    TOLERANCE RESISTANCE COVERPLATES
    9.
    发明申请
    TOLERANCE RESISTANCE COVERPLATES 有权
    耐受性覆盖

    公开(公告)号：US20160265372A1

    公开(公告)日：2016-09-15

    申请号：US14641470

    申请日：2015-03-09

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Ky H. Vu ,  Jeffrey J. DeGray ,  Ryan Alan Waite ,  Gina Cavallo ,  Thomas P. Dziuba

    IPC: F01D9/04 ,  F01D5/02 ,  F04D29/32 ,  F01D25/12

    CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/186 ,  F01D5/189 ,  F01D9/065 ,  F01D25/12 ,  F04D29/321 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/642 ,  F05D2240/126 ,  F05D2240/80 ,  F05D2260/20 ,  F05D2260/30 ,  Y02T50/676

    Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.

    Abstract translation: 燃气涡轮发动机部件组件包括相对于发动机中心轴线与第一部件周向间隔开的第一部件和第二部件。 第一挡板与第一部件相关联。 第二挡板与第二部件相关联。 第一和第二挡板中的每一个包括至少一个径向挡板。 在第一和第二挡板之间形成间隙以限定冷却空气入口。 第一盖板与第一挡板相关联以覆盖间隙的第一部分。 第二盖板与第二挡板相关联以覆盖间隙的第二部分。 第一和第二盖板彼此分开，并且包括至少一个盖板径向突片，其与相关联的至少一个挡板径向突片配合，以防止第一和第二挡板与第一和第二盖板之间的泄漏间隙。

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