公开(公告)号：US20210003020A1

公开(公告)日：2021-01-07

申请号：US17029807

申请日：2020-09-23

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Gregory Terrence Garay ,  Tingfan Pang ,  Helen Ogbazion Gabregiorgish ,  Zachary Daniel Webster ,  Steven Robert Brassfield

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/24 ,  F01D25/12

Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage fluidly coupling the inlet to the outlet.

公开(公告)号：US10830053B2

公开(公告)日：2020-11-10

申请号：US15818013

申请日：2017-11-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Gregory Terrence Garay ,  Zachary Daniel Webster ,  Kirk D. Gallier

IPC: F01D5/18

Abstract: An apparatus and method regarding an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction, at least one cooling passage extending radially within the interior and defining a primary cooling airflow, and at least one cooling hole having an inlet in communication with the cooling passage and an outlet in communication with the exterior of the outer wall.

公开(公告)号：US10605091B2

公开(公告)日：2020-03-31

申请号：US15194855

申请日：2016-06-28

Applicant: General Electric Company

Inventor： Gregory Terrence Garay ,  Douglas Ray Smith ,  Aaron Ezekiel Smith ,  Zachary Daniel Webster

IPC: F01D5/18 ,  B22C9/00 ,  B22C13/08

Abstract: An apparatus and method for forming a film hole in an outer wall of an airfoil. The film hole includes a blind opening adjacent the interior of the airfoil and a hole adjacent the exterior of the airfoil. The blind opening fluidly couples to the hole to form the film hole for providing a volume of fluid as a surface cooling film along the exterior of the outer wall.

公开(公告)号：US20200024951A1

公开(公告)日：2020-01-23

申请号：US16037662

申请日：2018-07-17

Applicant: GENERAL ELECTRIC COMPANY

Inventor： William Charles Herman ,  Jacob Romeo Rendon ,  Duane Allan Busch ,  Ryan Christopher Jones ,  Paul Christopher Schilling ,  Zachary Daniel Webster ,  Tingfan Pang ,  Gregory Terrence Garay ,  Steven Robert Brassfield

IPC: F01D5/08

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a passage. The cooling hole can include a laid back section where a coating can be applied. The method can include forming the cooling hole in the component and applying the coating to the component to maintain a specific geometry.

公开(公告)号：US10443395B2

公开(公告)日：2019-10-15

申请号：US15073687

申请日：2016-03-18

Applicant: General Electric Company

Inventor： Zachary Daniel Webster

IPC: F01D5/18 ,  F01D9/02 ,  F23R3/00 ,  F01D5/28

Abstract: An apparatus and method relating to a film hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film hole.

公开(公告)号：US20190257205A1

公开(公告)日：2019-08-22

申请号：US15898716

申请日：2018-02-19

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Zachary Daniel Webster ,  Gregory Terrence Garay ,  Kevin Robert Feldmann ,  Steven Robert Brassfield

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

Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.

公开(公告)号：US20190153870A1

公开(公告)日：2019-05-23

申请号：US15818013

申请日：2017-11-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Gregory Terrence Garay ,  Zachary Daniel Webster ,  Kirk D. Gallier

IPC: F01D5/18

Abstract: An apparatus and method regarding an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction, at least one cooling passage extending radially within the interior and defining a primary cooling airflow, and at least one cooling hole having an inlet in communication with the cooling passage and an outlet in communication with the exterior of the outer wall.

公开(公告)号：US20170191417A1

公开(公告)日：2017-07-06

申请号：US14989290

申请日：2016-01-06

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Robert Frederick Bergholz ,  Jason Randolph Allen ,  Robert David Briggs ,  Byron Andrew Pritchard, JR. ,  Kevin Robert Feldmann ,  Curtis Walton Stover ,  Zachary Daniel Webster ,  Fernando Reiter ,  Michael Alan Meade

IPC: F02C7/12 ,  F23R3/00 ,  F01D5/14 ,  F01D25/24 ,  F01D25/08 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D9/065 ,  F01D25/12 ,  F05D2240/11 ,  F05D2250/21 ,  F05D2250/22 ,  F05D2250/23 ,  F05D2250/232 ,  F05D2250/241 ,  F05D2250/27 ,  F05D2260/201 ,  F05D2260/2214 ,  F23R3/005 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/672 ,  Y02T50/676

Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, and a second engine component having a first surface in fluid communication with a cooling fluid flow and a second surface spaced from the cooling surface to define a space. A cooling aperture extends through the second engine component. A cooling feature extends from the cooling surface of the first engine component, and is oriented relative to the cooling aperture such that the cooling fluid flow is orthogonal and non-orthogonal to different portions of the cooling feature.

公开(公告)号：US20170159452A1

公开(公告)日：2017-06-08

申请号：US14958082

申请日：2015-12-03

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Zachary Daniel Webster

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

CPC classification number: F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/231 ,  F05D2260/202 ,  F05D2260/2212 ,  Y02T50/676

Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.