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公开(公告)号：US11499479B2
公开(公告)日：2022-11-15
申请号：US16057892
申请日：2018-08-08
Inventor： Kenneth Arthur Gould , Abdus Shamim , Jaroslaw Henryk Dekowski , Piotr Sebastian Hance , Przemyslaw Slawomir Tkaczyk , Marcin Pawel Faber , Adam Krysztopa , Piotr Lech Bar , Krzysztof Chelstowski , Craig Alan Gonyou , Robert John Parks
Abstract: A gas turbine engine having an improved air delivery system that includes features for pressurizing and/or cooling various components of the engine while minimizing the impact to the cycle efficiency of the engine, reducing the weight of the engine, and reducing the specific fuel consumption of the engine is provided.
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公开(公告)号：US11920500B2
公开(公告)日：2024-03-05
申请号：US17461113
申请日：2021-08-30
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Yu-Liang Lin , Craig Alan Gonyou , Scott Alan Schimmels , Jeffrey Douglas Rambo , Brian Gregg Feie
CPC classification number: F01D9/06 , F01D5/081 , F05D2240/128 , F05D2260/232 , F05D2260/606
Abstract: A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.
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公开(公告)号：US10738707B2
公开(公告)日：2020-08-11
申请号：US14935758
申请日：2015-11-09
Applicant: General Electric Company
Inventor： William Thomas Bennett , Kevin Samuel Klasing , Craig Alan Gonyou
Abstract: A gas turbine engine includes a combustion section space between a compressor section in a turbine section. The combustion section defines a combustion chamber and includes a combustor member defining an opening to the combustion chamber. A mounting assembly extends around or is positioned adjacent to the opening defined by the combustor member. In igniter extends through a ferrule of the mounting assembly and includes a distal end positioned proximate the opening in the combustor member. The igniter defines a plurality of channels each channel extending between a first end and a second end. The first end is positioned away from the distal end of the igniter relative to the second end, and the second end is a terminal end spaced from the distal end of the igniter.
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公开(公告)号：US20200224539A1
公开(公告)日：2020-07-16
申请号：US16249285
申请日：2019-01-16
Applicant: General Electric Company
Inventor： Anquan Wang , Ryan Christopher Jones , Paul Christopher Schilling , Craig Alan Gonyou
IPC: F01D5/18
Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.
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公开(公告)号：US20240200463A1
公开(公告)日：2024-06-20
申请号：US18586765
申请日：2024-02-26
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Yu-Liang Lin , Craig Alan Gonyou , Scott Alan Schimmels , Jeffrey Douglas Rambo , Brian Gregg Feie
CPC classification number: F01D9/06 , F01D5/081 , F05D2240/128 , F05D2260/232 , F05D2260/606
Abstract: A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.
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Patent Agency Ranking
公开(公告)号：US20240102392A1
公开(公告)日：2024-03-28
申请号：US18536428
申请日：2023-12-12
Applicant: General Electric Company
Inventor： Anquan Wang , Ryan Christopher Jones , Paul Christopher Schilling , Craig Alan Gonyou
IPC: F01D5/18
CPC classification number: F01D5/186
Abstract: An apparatus relating to a component for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow. The component having a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. At least one cooling hole including a connecting passage extending from a first inlet located at the cooled surface, to a first outlet located at the heated surface, the connecting passage defining a downstream flow direction from the first inlet to the first outlet, the connecting passage comprising a metering section fluidly coupled to the first inlet and defining a metered centerline and a diffusing section, downstream of the metering section, defining a diffused centerline, and fluidly coupling the metering section to the first outlet.
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公开(公告)号：US20230036206A1
公开(公告)日：2023-02-02
申请号：US17389503
申请日：2021-07-30
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Jonathan Russell Ratzlaff , Craig Alan Gonyou
Abstract: A gas turbine engine includes a combustion section, a turbine section, and a compressor section. The combustion section includes a combustor casing, a combustor, a cooling duct, and an outer duct. The combustor casing defines at least in part a diffuser cavity and a fluid inlet. The combustor disposed is in the diffuser cavity. The cooling duct is in fluid communication with the fluid inlet in the combustor casing and is configured to transport a flow of cooled air. The outer duct surrounds at least a portion of the cooling duct and extends along a portion of an entire length of the cooling duct. The outer duct defines a gap with the cooling duct and is configured to transport a flow of buffer air. The turbine section is disposed downstream from the combustion section. The cooling duct is in fluid communication with the turbine section.
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公开(公告)号：US20220128007A1
公开(公告)日：2022-04-28
申请号：US17571609
申请日：2022-01-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Craig Alan Gonyou , Nathan Joel Mullenix , Fei Huang
Abstract: A leakage management assembly for an orifice configured to limit a flow of at least one of a leakage fluid and a cooling fluid past an instrument positioned within the orifice are provided. The leakage management assembly includes a labyrinth ferrule including an annular ferrule body having a central bore extending therethrough. The labyrinth ferrule further includes an annular assembly cone formed at a first end of the labyrinth ferrule. The annular assembly cone includes an annular convergent lip and is configured to facilitate directing the instrument into the central bore. The labyrinth ferrule also includes a plurality of labyrinthine annular restrictions extending from a radially inner surface of the annular body toward the central bore. A combustor and a gas turbine engine including such a seal assembly are also provided.
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公开(公告)号：US10822958B2
公开(公告)日：2020-11-03
申请号：US16249285
申请日：2019-01-16
Applicant: General Electric Company
Inventor： Anquan Wang , Ryan Christopher Jones , Paul Christopher Schilling , Craig Alan Gonyou
IPC: F01D5/18
Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.
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公开(公告)号：US20170130653A1
公开(公告)日：2017-05-11
申请号：US14935758
申请日：2015-11-09
Applicant: General Electric Company
Inventor： William Thomas Bennett , Kevin Samuel Klasing , Craig Alan Gonyou
IPC: F02C7/264
Abstract: A gas turbine engine includes a combustion section space between a compressor section in a turbine section. The combustion section defines a combustion chamber and includes a combustor member defining an opening to the combustion chamber. A mounting assembly extends around or is positioned adjacent to the opening defined by the combustor member. In igniter extends through a ferrule of the mounting assembly and includes a distal end positioned proximate the opening in the combustor member. The igniter defines a plurality of channels each channel extending between a first end and a second end. The first end is positioned away from the distal end of the igniter relative to the second end, and the second end is a terminal end spaced from the distal end of the igniter.
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