公开(公告)号：US11173542B2

公开(公告)日：2021-11-16

申请号：US15636389

申请日：2017-06-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Xi Yang ,  Michael Cole ,  Michael Brown ,  Gregory Terrence Garay ,  Tingfan Pang ,  Brian David Przeslawski ,  Douglas Gerard Konitzer

IPC: B22C9/10 ,  B22C9/04 ,  B22C9/24 ,  B28B1/00 ,  B22D29/00 ,  B33Y10/00 ,  B33Y80/00 ,  C04B35/14 ,  B32B18/00 ,  B28B7/34

Abstract: A method of forming a cast component and a method of forming a casting mold. The method is performed by connecting at least one wax gate component to a ceramic core-shell mold. The ceramic core-shell mold includes at least a filter, first core portion, a first shell portion, and at least one first cavity between the core portion and the first shell portion. The core-shell mold may be manufactured using an additive manufacturing process and may include an integrated ceramic filter. At least a portion of the ceramic core-shell mold and the wax gate component is coated with a second ceramic material. The wax gate component is then removed to form a second cavity in fluid communication with the first cavity.

公开(公告)号：US20210239005A1

公开(公告)日：2021-08-05

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.

公开(公告)号：US20210239004A1

公开(公告)日：2021-08-05

申请号：US17078330

申请日：2020-10-23

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. The airfoil further comprising 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 defining a first cross-sectional area, the inlet in communication with the cooling passage, an outlet defining a second cross-sectional area greater than the first cross-sectional area; wherein the primary cooling airflow enters the inlet in a first direction and exits the outlet in a second direction different than the first direction.

公开(公告)号：US20210229163A1

公开(公告)日：2021-07-29

申请号：US17228168

申请日：2021-04-12

Applicant: General Electric Company

Inventor： Xi Yang ,  Michael Cole ,  Michael Brown ,  Gregory Terrence Garay ,  Tingfan Pang ,  Brian David Przeslawski ,  Douglas Gerard Konitzer

IPC: B22C9/10 ,  B28B1/00 ,  B22C9/04 ,  B22D29/00 ,  B33Y10/00 ,  B33Y80/00 ,  C04B35/622 ,  B28B7/34

Abstract: The present disclosure relates to a method of forming a cast component and a method of forming a casting mold. The method is performed by connecting at least one wax gate component to a ceramic core-shell mold. The ceramic core-shell mold includes at least a filter, first core portion, a first shell portion, and at least one first cavity between the core portion and the first shell portion. The core-shell mold may manufactured using an additive manufacturing process and may include an integrated ceramic filter. At least a portion of the ceramic core-shell mold and the wax gate component is coated with a second ceramic material. The wax gate component is then removed to form a second cavity in fluid communication with the first cavity.

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：US10702958B2

公开(公告)日：2020-07-07

申请号：US15439451

申请日：2017-02-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Gregory Terrence Garay ,  Mark Kevin Meyer ,  Douglas Gerard Konitzer ,  William Thomas Carter

IPC: F01D5/00 ,  B22F5/04 ,  B23K20/22 ,  F01D5/14 ,  B22F7/06 ,  B22C9/24 ,  B22D29/00 ,  B23P15/04 ,  B33Y80/00 ,  B23K26/34 ,  B22F3/105 ,  B23P6/04 ,  B23P6/00 ,  B23K35/02 ,  B23K26/0622 ,  B22F7/08 ,  B22C9/04 ,  B23K101/00 ,  B23K103/08 ,  B23K103/18

Abstract: Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the least the ceramic core serves as a build surface for a subsequent process of additively manufacturing the tip portions. The build surface is created by removing a top portion of the airfoil and the core, or by placing an ultra-thin shim on top of the airfoil and the core. The overhang projected by the shim is subsequently removed. These methods are not limited to turbine engine applications, but can be applied to any metallic object that can benefit from casting and additive manufacturing processes. The present disclosure also relates to finished and intermediate products prepared by these methods.

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：US10391549B2

公开(公告)日：2019-08-27

申请号：US15636404

申请日：2017-06-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Xi Yang ,  Michael Cole ,  Michael Brown ,  Gregory Terrence Garay ,  Tingfan Pang ,  Brian David Przeslawski ,  Douglas Gerard Konitzer

IPC: B22C9/04 ,  B22C9/10 ,  B28B1/00 ,  B22D29/00 ,  B33Y10/00 ,  B33Y80/00 ,  B28B11/04

Abstract: A method of forming a cast component and a method of forming a casting mold is generally provided. The method is performed by plugging or covering an opening in a ceramic core-shell mold. The ceramic core-shell mold includes at least a first core portion, a first shell portion, and at least one first cavity between the core portion and the first shell portion. The core-shell mold may be manufactured using an additive manufacturing process. At least a portion of the ceramic core-shell mold and the plug or cover is coated with a second ceramic material.