公开(公告)号：US09863259B2

公开(公告)日：2018-01-09

申请号：US14708939

申请日：2015-05-11

Applicant: United Technologies Corporation

Inventor： Mark A. Boeke ,  Kevin Rajchel ,  Mosheshe Camara-khary Blake ,  Vincent E. Simms

IPC: F01D9/04 ,  F04D11/00 ,  F01D11/00 ,  F01D25/24

CPC classification number: F01D9/042 ,  F01D11/006 ,  F01D25/246 ,  F05D2240/57

Abstract: An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.

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.

IPC: F01D5/18 ,  F01D9/04

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.

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.

IPC: F01D25/12 ,  F01D9/02

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.

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.

IPC: F01D5/18 ,  F01D9/04

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.

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.

IPC: F01D25/12 ,  F01D9/02

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.

公开(公告)号：US20160333712A1

公开(公告)日：2016-11-17

申请号：US14708939

申请日：2015-05-11

Applicant: United Technologies Corporation

Inventor： Mark A. Boeke ,  Kevin Rajchel ,  Mosheshe Camara-khary Blake ,  Vincent E. Simms

IPC: F01D11/00 ,  F01D9/04

CPC classification number: F01D9/042 ,  F01D11/006 ,  F01D25/246 ,  F05D2240/57

Abstract: An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.

Abstract translation: 用于燃气涡轮发动机的翼型件包括第一翼型件。 第一和弦密封件位于翼型件的第一端附近。 第二弦编密封位于翼型的第二端附近。 第一弦音密封包括平行于第二弦音密封件上的第一边缘的第一边缘。