公开(公告)号：US20190257205A1

公开(公告)日：2019-08-22

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：US20190153870A1

公开(公告)日：2019-05-23

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：US20190017391A1

公开(公告)日：2019-01-17

申请号：US15648541

申请日：2017-07-13

Applicant: General Electric Company

Inventor： Thomas Earl Dyson ,  Nicholas William Rathay ,  Brendon James Leary ,  Gregory Terrence Garay ,  Gustavo Adolfo Ledezma ,  David Wayne Weber ,  Aaron Ezekiel Smith

IPC: F01D5/18 ,  F01D5/14

Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.

公开(公告)号：US20180363468A1

公开(公告)日：2018-12-20

申请号：US15622266

申请日：2017-06-14

Applicant: General Electric Company

Inventor： Matthew Thomas Beyer ,  Gregory Terrence Garay ,  Tingfan Pang ,  Aaron Ezekiel Smith

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F23R3/00 ,  F02C7/12

Abstract: An apparatus and method for cooling an airfoil or engine component can include an outer wall defining an interior. A cooling circuit can be provided in the interior for directing flow of fluid and defining a flow direction. A plurality of cooling conduits can be arranged in the cooling circuit and organized into two or more sets of rows.

公开(公告)号：US20180298765A1

公开(公告)日：2018-10-18

申请号：US15487981

申请日：2017-04-14

Applicant: General Electric Company

Inventor： Matthew Thomas Beyer ,  Gregory Terrence Garay ,  Kirk D. Gallier ,  Toby George Darkins, JR.

IPC: F01D5/20 ,  F01D5/28 ,  F01D5/30

Abstract: An apparatus and method for a replaceable tip element of an airfoil in a turbine engine. The airfoil has an outer wall defining an interior and including 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, with the tip having a replaceable tip element.