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公开(公告)号：US11208901B2
公开(公告)日：2021-12-28
申请号：US16423313
申请日：2019-05-28
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Zachary Daniel Webster
Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.
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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
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.
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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.
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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
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.
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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.
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Patent Agency Ranking
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
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.
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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.
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公开(公告)号：US10443395B2
公开(公告)日：2019-10-15
申请号：US15073687
申请日：2016-03-18
Applicant: General Electric Company
Inventor： Zachary Daniel Webster
Abstract: An apparatus and method relating to a film hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film hole.
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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
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.
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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.
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