公开(公告)号：US12215602B2

公开(公告)日：2025-02-04

申请号：US18599486

申请日：2024-03-08

Applicant: General Electric Company

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

IPC: F01D5/18 ,  F01D9/02 ,  F01D9/06

Abstract: A component for a turbine engine comprises a wall having a first wall surface and a second wall surface; and a cooling hole comprising a connecting passage extending between an inlet at the first wall surface and an outlet located at the second wall surface. The connecting passage includes: a metering section extending from the inlet toward the outlet and defining a centerline, and a diffusing section at the outlet defining first and second side walls, a first junction between the first side wall and the metering section and a second junction between the second side wall the metering section, the first side wall extending between the first junction and the outlet, and the second side wall extending between the second junction and the outlet. A metering section distance is measured between the centerline and a metering section wall of the metering section.

公开(公告)号：US20240401483A1

公开(公告)日：2024-12-05

申请号：US18326684

申请日：2023-05-31

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Kirk Douglas Gallier ,  Zachary Daniel Webster ,  Brian Kenneth Corsetti

IPC: F01D5/18

Abstract: An airfoil assembly for a turbine engine which generates a hot fluid flow and provides a cooling fluid flow. The airfoil assembly includes a platform with radially spaced upper and lower walls, the platform extending between a platform leading edge and a platform trailing edge to define an axial direction and extending between a pair of slash faces, an airfoil having an airfoil wall extending radially between a root and a tip to define a span length, the platform wall extending from the airfoil wall proximate the root. A fillet extends between the heated surface and the airfoil wall and defines at least a portion of the root. The airfoil assembly further includes a set of film holes.

公开(公告)号：US11988109B2

公开(公告)日：2024-05-21

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 ,  F01D5/08

CPC classification number: F01D5/187 ,  F01D5/087 ,  F05D2240/307 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/232

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：US11879356B2

公开(公告)日：2024-01-23

申请号：US17852875

申请日：2022-06-29

Applicant: General Electric Company

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Kevin Robert Feldmann

IPC: F01D5/18 ,  F01D5/14 ,  F01D11/12 ,  F01D5/28 ,  F01D1/12 ,  F01D11/14

CPC classification number: F01D5/186 ,  F01D1/12 ,  F01D5/147 ,  F01D5/284 ,  F01D11/122 ,  F01D11/14 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/311 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2300/514

Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

公开(公告)号：US20230399953A1

公开(公告)日：2023-12-14

申请号：US17836023

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 ,  F01D25/12

CPC classification number: F01D5/186 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/202

Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (θ) with the heated surface.

公开(公告)号：US11174736B2

公开(公告)日：2021-11-16

申请号：US16224065

申请日：2018-12-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Tingfan Pang ,  Kirk D. Gallier

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/30 ,  B22F10/20 ,  B33Y10/00 ,  B33Y80/00 ,  B22F10/30

Abstract: Aspects generally relate to a method of forming a plexus within an additively-manufactured component. The method includes forming a fluid passage in the plexus by serially forming layers of material along a build direction to form a column defining the fluid passage along a first direction within an interior of a turbine engine component.

公开(公告)号：US20210220904A1

公开(公告)日：2021-07-22

申请号：US17221911

申请日：2021-04-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Tingfan Pang ,  Gregory Terrence Garay ,  Zachary Daniel Webster ,  Ryan Christopher Jones

IPC: B22C9/10 ,  B22C9/12 ,  B22C9/26 ,  B22C7/02 ,  B22C21/14 ,  F01D5/18 ,  B28B7/34 ,  B28B1/00

Abstract: A leachable casting core and method of manufacture may include a plurality of legs configured to establish a plurality of internal flow channels of a cast component. Tie bars, with a first tie bar end and a second tie bar end opposite thereof, may couple to at least two of the plurality of legs. At least one of the tie bars may be oriented to form a linking cavity within the cast component between the internal flow channels. The linking cavity may serve as an obstruction to fluid communication through the linking cavity.

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：US20210148242A1

公开(公告)日：2021-05-20

申请号：US17158670

申请日：2021-01-26

Applicant: General Electric Company

Inventor： Ryan Christopher Jones ,  Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Tingfan Pang

IPC: F01D11/00 ,  F01D9/04

Abstract: A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.

公开(公告)号：US20200347735A1

公开(公告)日：2020-11-05

申请号：US16929936

申请日：2020-07-15

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/18

Abstract: An airfoil for a turbine engine, comprising an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side 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, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.