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公开(公告)号：US10760431B2
公开(公告)日：2020-09-01
申请号：US15697886
申请日：2017-09-07
Applicant: General Electric Company
Inventor： Zachary Daniel Webster , Aaron Ezekiel Smith , Kirk D. Gallier
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.
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公开(公告)号：US10590778B2
公开(公告)日：2020-03-17
申请号：US15667787
申请日：2017-08-03
Applicant: General Electric Company
Inventor： Emily Rosette Clark , Weston Nolan Dooley , Kirk D. Gallier
Abstract: An apparatus and method for cooling an engine component such as an airfoil can include an outer wall separating a cooling fluid flow from a hot flow. A cooling circuit can be provided in the engine component including a cooling passage having at least one pin within the cooling passage with a chevron shape and a non-uniform configuration.
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公开(公告)号：US10569481B2
公开(公告)日：2020-02-25
申请号：US15632739
申请日：2017-06-26
Applicant: General Electric Company
Inventor： Kirk D. Gallier , Nathan Carl Sizemore
IPC: B29C70/30 , F01D5/28 , F01D5/18 , B32B18/00 , B29C70/54 , B29D99/00 , B32B5/02 , B29L31/08 , B32B1/00
Abstract: Ply layups and methods for forming composite components are provided. For example, a method for forming a composite component comprises laying up a plurality of composite plies to form a composite ply layup; partially processing the composite ply layup to form a green state layup; machining the green state layup; assembling the green state layup with one or more sub-assemblies; and processing the green state layup and the one or more sub-assemblies to form the composite component. In an exemplary embodiment, the composite component is a turbine nozzle airfoil. Another exemplary method comprises laying up a plurality of composite plies to form a composite ply layup; compacting the composite ply layup to form a green state layup; machining the green state layup; assembling the green state layup with one or more sub-assemblies; and processing the green state layup and the one or more sub-assemblies to form the composite component.
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公开(公告)号：US20190071976A1
公开(公告)日：2019-03-07
申请号：US15697886
申请日：2017-09-07
Applicant: General Electric Company
Inventor： Zachary Daniel Webster , Aaron Ezekiel Smith , Kirk D. Gallier
CPC classification number: F01D5/186 , F01D9/023 , F01D9/041 , F01D9/065 , F01D25/12 , F02K1/822 , F05D2220/323 , F05D2230/50 , F05D2240/11 , F05D2240/124 , F05D2240/306 , F05D2240/81 , F05D2250/73 , F05D2260/202 , F23R3/002 , F23R2900/03042
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.
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公开(公告)号：US20190040748A1
公开(公告)日：2019-02-07
申请号：US15667787
申请日：2017-08-03
Applicant: General Electric Company
Inventor： Emily Rosette Clark , Weston Nolan Dooley , Kirk D. Gallier
Abstract: An apparatus and method for cooling an engine component such as an airfoil can include an outer wall separating a cooling fluid flow from a hot flow. A cooling circuit can be provided in the engine component including a cooling passage having at least one pin within the cooling passage with a chevron shape and a non-uniform configuration.
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Patent Agency Ranking
公开(公告)号：US09995160B2
公开(公告)日：2018-06-12
申请号：US14578816
申请日：2014-12-22
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Kirk D. Gallier , Robert Frederick , Darrell Senile , Benjamin Huizenga
CPC classification number: F01D9/065 , F01D5/282 , F01D5/284 , F01D11/005 , F01D25/162 , F05D2300/6033 , Y02T50/672
Abstract: An airfoil profile-shaped seal is disposable between an inside surface of a hollow airfoil body and a seal support. The seal includes an elongated member defining a generally closed curve having a generally straight portion, a generally curved portion, and having a solid cross-section across and along the length of the elongated member. When the seal is disposed in an airfoil profile-shaped groove of a seal support adjacent to the inner surface of the hollow airfoil body, and a fluid pressure on one side of the seal is greater than a fluid pressure on the other side of the seal, portions of the seal engage the inner surface of the hollow airfoil body and a surface of the groove to form a seal to inhibit leakage of fluid from the one side to the other side.
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公开(公告)号：US20240247590A1
公开(公告)日：2024-07-25
申请号：US18599486
申请日：2024-03-08
Applicant: General Electric Company
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D9/065 , F05D2230/10 , F05D2260/202
Abstract: A component for a turbine engine comprises a wall having a first wall surface and a second wall surface; and a cooling hole comprising a connecting passage extending between an inlet at the first wall surface and an outlet located at the second wall surface. The connecting passage includes: a metering section extending from the inlet toward the outlet and defining a centerline, and a diffusing section at the outlet defining first and second side walls, a first junction between the first side wall and the metering section and a second junction between the second side wall the metering section, the first side wall extending between the first junction and the outlet, and the second side wall extending between the second junction and the outlet. A metering section distance is measured between the centerline and a metering section wall of the metering section.
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公开(公告)号：US11927110B2
公开(公告)日：2024-03-12
申请号：US17582305
申请日：2022-01-24
Applicant: General Electric Company
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D9/065 , F05D2230/10 , F05D2260/202
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.
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公开(公告)号：US11549377B2
公开(公告)日：2023-01-10
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：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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