公开(公告)号：US20190085706A1

公开(公告)日：2019-03-21

申请号：US15707464

申请日：2017-09-18

Applicant: General Electric Company

Inventor： Zachary Daniel Webster ,  Kirk D. Gallier

IPC: F01D5/18 ,  F01D9/04

Abstract: An airfoil assembly for a turbine engine can include a platform having a fore edge, an aft edge axially spaced from the fore edge, and opposing heated and cooled surfaces. An airfoil can extend from the heated surface of the platform, and a cooling cavity can be positioned interiorly of the platform.

公开(公告)号：US20170370229A1

公开(公告)日：2017-12-28

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 ,  F01D9/02 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F01D25/12

CPC classification number: F01D5/186 ,  B22C9/00 ,  B22C13/085

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：US20170268346A1

公开(公告)日：2017-09-21

申请号：US15073687

申请日：2016-03-18

Applicant: General Electric Company

Inventor： Zachary Daniel Webster

IPC: F01D5/18 ,  F23R3/00 ,  F01D9/02

CPC classification number: F01D5/186 ,  F01D5/288 ,  F01D9/02 ,  F05D2220/30 ,  F05D2230/12 ,  F05D2230/13 ,  F05D2230/21 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2250/141 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2300/6033 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

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：US20250163813A1

公开(公告)日：2025-05-22

申请号：US18514499

申请日：2023-11-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Brian Kenneth Corsetti ,  Zachary Daniel Webster ,  Kirk Douglas Gallier ,  Daniel Endecott Osgood ,  Susan Emily Schulz

IPC: F01D5/18

Abstract: An airfoil assembly for a turbine engine, the airfoil assembly including a platform having an upper surface and a lower surface that are spaced from one another in a radial direction; a leading edge and trailing edge that are spaced from one another in an axial direction; and a first slash face and a second slash face that are spaced from one another in a circumferential direction. An airfoil can extend in from the platform in a radial direction. A platform chamber can be defined at least partially between the upper surface and the lower surface. The platform can include an impingement channel.

公开(公告)号：US11898460B2

公开(公告)日：2024-02-13

申请号：US17836049

申请日：2022-06-09

Applicant: General Electric Company

Inventor： Jonathan Michael Rausch ,  Zachary Daniel Webster ,  Kevin Robert Feldmann ,  Andrew David Perry ,  Kirk Douglas Gallier ,  Daniel Endecott Osgood

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/30 ,  F05D2260/202

Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.

公开(公告)号：US11885236B2

公开(公告)日：2024-01-30

申请号：US17714629

申请日：2022-04-06

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/18 ,  F01D5/20 ,  F01D5/30

CPC classification number: F01D5/187 ,  F01D5/20 ,  F01D5/3007 ,  F05D2240/304 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2240/307 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202

Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.

公开(公告)号：US20230175405A1

公开(公告)日：2023-06-08

申请号：US17973976

申请日：2022-10-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Zachary Daniel Webster ,  Daniel Endecott Osgood ,  Kirk Douglas Gallier

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/307 ,  F05D2260/20

Abstract: An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.

公开(公告)号：US11560803B1

公开(公告)日：2023-01-24

申请号：US17520146

申请日：2021-11-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Kirk Douglas Gallier ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Daniel Lee Durstock ,  Ricardo Caraballo

IPC: F01D5/18 ,  F01D5/08

Abstract: An engine component for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side. The engine component further comprising at least one cooling conduit provided in the interior and having conduit sidewalls and a set of cooling passages formed in the wall and fluidly coupling the at least one cooling conduit to the outer surface, at least one of the cooling passages in the set comprising a primary cooling passage portion and a secondary cooling passage portion. A diffusion slot located in the primary cooling passage portion and an impingement zone fluidly coupled to the diffusion slot.

公开(公告)号：US11486259B1

公开(公告)日：2022-11-01

申请号：US17519958

申请日：2021-11-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Kirk Douglas Gallier ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Nicholas William Rathay ,  Daniel Lee Durstock

IPC: F01D5/18

Abstract: An engine component for a turbine engine comprising a wall defining an interior and having an outer surface over which flows the combustion airflow. The outer surface defining a first side and a second side extending between an upstream edge and a downstream edge and extending between a root and a tip. At least one cooling conduit provided in the interior and having conduit sidewalls; a set of cooling passages with at least one of the cooling passages in the set comprising: a first cooling passage portion having a surface outlet opening on the surface; a second cooling passage portion, intersecting the first cooling passage portion, and having an inlet fluidly coupled to the cooling conduit and an intermediate outlet fluidly connecting the second cooling passage portion to the first cooling passage at the intersection. The cooling passage comprising at least one fillet.

公开(公告)号：US11448076B2

公开(公告)日：2022-09-20

申请号：US17213771

申请日：2021-03-26

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/18

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.