公开(公告)号：US10370978B2

公开(公告)日：2019-08-06

申请号：US14884114

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Steven Robert Brassfield ,  Robert Frederick Bergholz ,  Aaron Ezekiel Smith ,  Weston Nolan Dooley

IPC: F01D5/18 ,  F01D5/30 ,  F01D9/04 ,  F01D25/12

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

公开(公告)号：US20180291743A1

公开(公告)日：2018-10-11

申请号：US15481659

申请日：2017-04-07

Applicant: General Electric Company

Inventor： James Michael Hoffman ,  Weston Nolan Dooley ,  Matthew Lee Krumanaker ,  Aaron Ezekiel Smith ,  Steven Robert Brassfield

IPC: F01D5/08 ,  F01D5/18

Abstract: A turbine engine can include an airfoil comprising an outer wall bounding an interior, as well as an airfoil cooling circuit located within the interior and including a feed tube separating into at least first and second branches. A flow divider can be included in the airfoil and positioned to confront the feed tube.

公开(公告)号：US20170107826A1

公开(公告)日：2017-04-20

申请号：US14884075

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Weston Nolan Dooley ,  Steven Robert Brassfield ,  David Benjamin Helmer ,  Jeremy Clyde Bailey ,  Robert David Briggs

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/676

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

公开(公告)号：US12031442B2

公开(公告)日：2024-07-09

申请号：US18072921

申请日：2022-12-01

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Thomas Joseph Lipinski

IPC: F01D11/02 ,  F02C7/28

CPC classification number: F01D11/025 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55

Abstract: A turbine engine comprising an engine core, a plurality of circumferentially arranged vanes, and a floating seal. The plurality of circumferentially arranged vanes forming an upper band and a lower band. The floating seal being carried by at least one respective vane of the plurality of circumferentially arranged vanes. The floating seal having a ring and at least one dynamic seal.

公开(公告)号：US10364681B2

公开(公告)日：2019-07-30

申请号：US14884057

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Robert Frederick Bergholz ,  Aaron Ezekiel Smith ,  Weston Nolan Dooley

IPC: F01D5/18

Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.

公开(公告)号：US10174620B2

公开(公告)日：2019-01-08

申请号：US14884075

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Weston Nolan Dooley ,  Steven Robert Brassfield ,  David Benjamin Helmer ,  Jeremy Clyde Bailey ,  Robert David Briggs

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

公开(公告)号：US20230265762A1

公开(公告)日：2023-08-24

申请号：US18072921

申请日：2022-12-01

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Thomas Joseph Lipinski

IPC: F01D11/02 ,  F02C7/28

CPC classification number: F01D11/025 ,  F02C7/28 ,  F05D2240/55 ,  F05D2220/32

Abstract: A turbine engine comprising an engine core, a plurality of circumferentially arranged vanes, and a floating seal. The plurality of circumferentially arranged vanes forming an upper band and a lower band. The floating seal being carried by at least one respective vane of the plurality of circumferentially arranged vanes. The floating seal having a ring and at least one dynamic seal.

公开(公告)号：US20210270139A1

公开(公告)日：2021-09-02

申请号：US17324660

申请日：2021-05-19

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Weston Nolan Dooley ,  Steven Robert Brassfield

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12

Abstract: An airfoil for a gas turbine engine can include an outer surface defining a pressure side and a suction side extending axially between a leading edge and a trailing edge and extending radially between a first end and a second end to define a span-wise direction, and a cooling circuit located within the airfoil. The cooling circuit can include a cooling air inlet passage, a radially extending supply passage, an upstream supply passage fluidly coupling the cooling air inlet passage and the supply passage, and a near wall cooling mesh extending along a portion of the outer surface.

公开(公告)号：US20200024969A1

公开(公告)日：2020-01-23

申请号：US16214411

申请日：2018-12-10

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Weston Nolan Dooley ,  Steven Robert Brassfield

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

公开(公告)号：US20170107825A1

公开(公告)日：2017-04-20

申请号：US14884057

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Robert Frederick Bergholz ,  Aaron Ezekiel Smith ,  Weston Nolan Dooley

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2260/203 ,  F05D2260/941 ,  Y02T50/676

Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.