公开(公告)号：US10563519B2

公开(公告)日：2020-02-18

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：US20190186272A1

公开(公告)日：2019-06-20

申请号：US15844684

申请日：2017-12-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Zachary Daniel Webster ,  Aaron Ezekiel Smith ,  Steven Robert Brassfield

IPC: F01D5/18 ,  F23R3/00 ,  F01D5/14

CPC classification number: F01D5/186 ,  F01D5/141 ,  F05D2260/202 ,  F23R3/002

Abstract: An apparatus and method 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. The airfoil further includes at least one cooling hole including a diffusing section and fluidly coupling an exterior of the engine component to an exterior of the engine component.

公开(公告)号：US10315248B2

公开(公告)日：2019-06-11

申请号：US15354112

申请日：2016-11-17

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: B22D31/00 ,  B22D29/00 ,  B22D25/02 ,  B22C9/10 ,  B22C9/24 ,  F01D9/06

Abstract: The present disclosure generally relates to methods and apparatuses for forming cast parts having cast in features aligned with a casting core. The part is cast around a casting core within a casting shell. The casting core has a first feature that creates a corresponding second feature of the cast part. The casting core includes a third alignment feature that creates a corresponding fourth feature of the cast part spaced apart from the second feature of the cast part. A machining tool is aligned with the second feature of the cast part based on the fourth feature of the cast part. The machining tool machines the cast part to create the at least one passageway aligned with the second feature.

公开(公告)号：US20190145267A1

公开(公告)日：2019-05-16

申请号：US15814996

申请日：2017-11-16

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Aaron Ezekiel Smith ,  Fernando Reiter ,  Zachary Daniel Webster

IPC: F01D5/18 ,  F02C7/141 ,  F01D5/14

Abstract: An apparatus and method for a component for a turbine engine, which generates a hot gas flow, and provides a cooling fluid flow, comprising a wall separating the hot gas flow from the cooling fluid flow and having a heated surface along which the hot gas flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising a connecting passage extending between an inlet at the cooled surface and an outlet located at the heated surface, with the connecting passage comprising a diffusing section.

公开(公告)号：US20190071977A1

公开(公告)日：2019-03-07

申请号：US15697916

申请日：2017-09-07

Applicant: General Electric Company

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

IPC: F01D5/18 ,  F01D9/06

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 connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.

公开(公告)号：US20250154873A1

公开(公告)日：2025-05-15

申请号：US18941684

申请日：2024-11-08

Applicant: General Electric Company

Inventor： Zachary R. Noeth ,  Thomas P. Warburg ,  Zachary Daniel Webster ,  Kelli Marie Fishback ,  Marie Myers ,  Kurt Thomas Whittington

IPC: F01D5/18 ,  F01D5/14

Abstract: A gas turbine engine having a blade assembly with a platform, an airfoil, and a shank. The airfoil has a plurality of cooling conduits, and the shank has a plurality of inlet passages to provide cooling fluid to the cooling conduits in the airfoil. The cooling fluid is vented through a plurality of cooling holes along the trailing edge of the airfoil. The blade assembly has specific geometries that improve durability

公开(公告)号：US12286902B2

公开(公告)日：2025-04-29

申请号：US18418909

申请日：2024-01-22

Applicant: General Electric Company

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

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

Abstract: A component for a turbine engine includes a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine, a cooling passage defined within the body, and a trench on the exterior surface. The trench includes a plurality of outlets, and a plurality of cooling holes extending from the cooling passage to the corresponding plurality of outlets.

公开(公告)号：US20240066588A1

公开(公告)日：2024-02-29

申请号：US17898751

申请日：2022-08-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Craig Alan Gonyou ,  Daniel Lee Durstock ,  Kevin R. Feldmann ,  Kirk Douglas Gallier ,  William C. Herman ,  Nicholas Charles Gentilli

IPC: B22C9/10

CPC classification number: B22C9/10

Abstract: A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to:





(


D
⁢

1

eq
⁢
min




D
⁢

2

eq
⁢
min




)

⁢


(

R

D
⁢

2

eq
⁢
min




)

.

公开(公告)号：US20230399955A1

公开(公告)日：2023-12-14

申请号：US18354774

申请日：2023-07-19

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 ,  F05D2260/202 ,  F05D2240/30

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. One or more blades in the compressor or turbine sections has an internal cooling conduit with at least one of a bend or a terminal end. A plurality of cooling holes are provided in the blade, with each hole having an inlet fluidly coupled to the cooling conduit and an outlet opening onto an exterior of the blade.

公开(公告)号：US11352889B2

公开(公告)日：2022-06-07

申请号：US16223308

申请日：2018-12-18

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/18 ,  F01D5/20 ,  F01D5/30

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.