公开(公告)号：US20180142559A1

公开(公告)日：2018-05-24

申请号：US15360529

申请日：2016-11-23

Applicant: General Electric Company

Inventor： Jessica Elizabeth Coomer ,  Matthew Thomas Beyer ,  Stephen Molter ,  Aaron Ezekiel Smith

IPC: F01D5/18 ,  F01D5/30

CPC classification number: F01D5/187 ,  F01D5/20 ,  F01D5/3007 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2250/25 ,  F05D2250/70 ,  F05D2260/202 ,  F05D2260/203 ,  F05D2260/204

Abstract: A tip cooling apparatus for a turbine airfoil includes: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket defined by the tip walls; at least one feed hole passing through the tip cap or tip walls, communicating with the pocket; and a cooling matrix disposed in the pocket, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the pocket, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween.

公开(公告)号：US11236625B2

公开(公告)日：2022-02-01

申请号：US15615869

申请日：2017-06-07

Applicant: General Electric Company

Inventor： Matthew Thomas Beyer ,  Gregory Terrence Garay

IPC: F01D9/02 ,  B23P15/02 ,  F02C6/12

Abstract: A method for making a cooled component for a turbine engine includes casting an airfoil assembly having an airfoil with an airfoil cooling passage and extending from a platform with at least one platform cooling passage, and forming a connecting passage between the airfoil cooling air passage and the platform cooling air passage via a tool inserted into a breakout opening in a slashface of the platform.

公开(公告)号：US11015453B2

公开(公告)日：2021-05-25

申请号：US15820568

申请日：2017-11-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Aaron Ezekiel Smith ,  Matthew Thomas Beyer ,  Gregory Terrence Garay ,  Zachary Daniel Webster

IPC: F01D5/18 ,  F01D5/20 ,  F01D9/04 ,  F01D25/12 ,  F04D29/32 ,  F04D29/58 ,  F04D29/54 ,  F02C3/04 ,  F02C7/18

Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and extending in a chord-wise direction between a leading edge and a trailing edge, and also extending radially between a root and a tip. A tip rail including at least one tip cooling cavity can project from the tip, and cooling holes can be provided in the tip rail.

公开(公告)号：US10830057B2

公开(公告)日：2020-11-10

申请号：US15609488

申请日：2017-05-31

Applicant: General Electric Company

Inventor： Matthew Thomas Beyer ,  Gregory Terrence Garay ,  Aaron Ezekiel Smith

IPC: F01D5/20 ,  F01D5/18

Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail at the tip. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.

公开(公告)号：US20190153873A1

公开(公告)日：2019-05-23

申请号：US15820568

申请日：2017-11-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Aaron Ezekiel Smith ,  Matthew Thomas Beyer ,  Gregory Terrence Garay ,  Zachary Daniel Webster

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F02C3/04 ,  F02C7/18

Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and extending in a chord-wise direction between a leading edge and a trailing edge, and also extending radially between a root and a tip. A tip rail including at least one tip cooling cavity can project from the tip, and cooling holes can be provided in the tip rail.