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公开(公告)号：US10024172B2
公开(公告)日：2018-07-17
申请号：US14634006
申请日：2015-02-27
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Richard M. Salzillo , Jeffrey J. DeGray , Shawn J. Gregg
Abstract: An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface. A recess is in an interior surface of the airfoil wall adjacent the fillet. A baffle tube is located in the airfoil cavity spaced from the recess.
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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
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。
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公开(公告)号：US09080452B2
公开(公告)日：2015-07-14
申请号：US13630419
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Shawn J. Gregg , Sarah Riley , Jeffrey J. DeGray , Richard M. Salzillo
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D25/12 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.
Abstract translation: 用于燃气涡轮发动机的定子叶片包括沿径向延伸并由具有气体流路表面的平台支撑的翼型件。 冷却通道布置在平台中，并且包括流体连接到延伸通过平台的边缘的入口通道的圆周通道，以及从气体流路表面延伸到周向通道的膜冷却孔，通过边缘的径向延伸通道 的平台。 空隙与径向延伸通道和入口通道中的至少一个相互连接。
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公开(公告)号：US10648363B2
公开(公告)日：2020-05-12
申请号：US15856232
申请日：2017-12-28
Applicant: United Technologies Corporation
Inventor： Shawn M. McMahon , Christopher Whitfield , Nicholas M. LoRicco , Steven Bruce Gautschi , Vincent E. Simms , Justin M. Aniello , Thomas Allwood , Richard M. Salzillo , Jeffery Scott Hembree, Sr.
Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
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公开(公告)号：US10533425B2
公开(公告)日：2020-01-14
申请号：US15856182
申请日：2017-12-28
Applicant: United Technologies Corporation
Inventor： Shawn M. McMahon , Christopher Whitfield , Nicholas M. LoRicco , Steven Bruce Gautschi , Vincent E. Simms , Justin M. Aniello , Thomas Allwood , Richard M. Salzillo , Jeffery Scott Hembree, Sr.
Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.
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Patent Agency Ranking
公开(公告)号：US20190203602A1
公开(公告)日：2019-07-04
申请号：US15856182
申请日：2017-12-28
Applicant: United Technologies Corporation
Inventor： Shawn M. McMahon , Christopher Whitfield , Nicholas M. LoRicco , Steven Bruce Gautschi , Vincent E. Simms , Justin M. Aniello , Thomas Allwood , Richard M. Salzillo , Jeffery Scott Hembree, SR.
CPC classification number: F01D5/186 , F01D9/041 , F01D9/065 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/202
Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.
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公开(公告)号：US10273820B2
公开(公告)日：2019-04-30
申请号：US15295268
申请日：2016-10-17
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Mark A. Boeke , Jeffrey J. DeGray , Richard M. Salzillo , Dominic J. Mongillo
IPC: F01D9/06
Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
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公开(公告)号：US10072517B2
公开(公告)日：2018-09-11
申请号：US14769210
申请日：2014-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark A. Boeke , Kevin Rajchel , Richard M. Salzillo , Jeffrey J. Degray , Allison Mainelli
CPC classification number: F01D11/005 , F01D9/041 , F05D2240/11 , F05D2240/57
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.
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公开(公告)号：US20190203612A1
公开(公告)日：2019-07-04
申请号：US15856232
申请日：2017-12-28
Applicant: United Technologies Corporation
Inventor： Shawn M. McMahon , Christopher Whitfield , Nicholas M. LoRicco , Steven Bruce Gautschi , Vincent E. Simms , Justin M. Aniello , Thomas Allwood , Richard M. Salzillo , Jeffery Scott Hembree, SR.
CPC classification number: F01D25/12 , F01D9/02 , F05D2220/32 , F05D2250/74 , F05D2260/202
Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
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公开(公告)号：US20180106156A1
公开(公告)日：2018-04-19
申请号：US15295268
申请日：2016-10-17
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Mark A. Boeke , Jeffrey J. DeGray , Richard M. Salzillo , Dominic J. Mongillo
CPC classification number: F01D9/065 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
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