公开(公告)号：US20190249554A1

公开(公告)日：2019-08-15

申请号：US15895157

申请日：2018-02-13

Applicant: GENERAL ELECTRIC COMPANY

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

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

CPC classification number: F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/323 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/202

Abstract: An apparatus and method for 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, an outlet located proximate the leading edge, with a connecting passage fluidly coupling the inlet to the outlet.

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.

公开(公告)号：US20190085705A1

公开(公告)日：2019-03-21

申请号：US15707303

申请日：2017-09-18

Applicant: General Electric Company

Inventor： Zachary Daniel Webster ,  Daniel Scott Martyn ,  Aaron Ezekiel Smith ,  Kirk D. Gallier

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

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

公开(公告)号：US20250027417A1

公开(公告)日：2025-01-23

申请号：US18440316

申请日：2024-02-13

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 ,  F01D5/14 ,  F01D9/04

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：US20240337190A1

公开(公告)日：2024-10-10

申请号：US18295388

申请日：2023-04-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Susan Emily Schulz ,  Zachary Daniel Webster ,  Daniel Endecott Osgood ,  Jorge Rodrigo Quintero Badillo ,  Catherine Marie Rucki ,  Ricardo Caraballo ,  David Lawrence Holzschuh

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/188 ,  F01D5/147 ,  F05D2240/81 ,  F05D2260/201

Abstract: A turbine blade assembly for a turbine engine that generates a hot fluid flow and provides a cooling fluid flow. The turbine blade assembly having a platform with an upper wall radially spaced from a lower wall, and a platform wall connecting the upper wall to the lower wall to bound an interior of the platform. An airfoil extending from the upper wall and having an airfoil wall at least partially bounding an interior of the airfoil and defining a heated surface in contact with the hot fluid flow. At least one cooling supply conduit extending into the interior of the airfoil and multiple cores provided in the interior of the platform.

公开(公告)号：US20240254885A1

公开(公告)日：2024-08-01

申请号：US18599470

申请日：2024-03-08

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：US11639664B2

公开(公告)日：2023-05-02

申请号：US17837086

申请日：2022-06-10

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.

公开(公告)号：US11566527B2

公开(公告)日：2023-01-31

申请号：US16223735

申请日：2018-12-18

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/14 ,  F01D5/18

Abstract: A component, such as for a turbine engine, can include an airfoil with 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. The component can also include at least one cooling passage within the interior.

公开(公告)号：US11499433B2

公开(公告)日：2022-11-15

申请号：US16223279

申请日：2018-12-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster

IPC: F01D5/18 ,  F01D5/30

Abstract: A turbine engine airfoil and method of cooling includes 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. The airfoil can also include at least one cooling conduit and an impingement zone located within the at least one cooling conduit.

公开(公告)号：US11384642B2

公开(公告)日：2022-07-12

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.