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公开(公告)号：US11994039B2
公开(公告)日：2024-05-28
申请号：US17711405
申请日：2022-04-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Kirk Douglas Gallier , Charles William Craig, III
CPC classification number: F01D25/246 , F01D9/042 , F01D11/005 , F05D2300/6033 , Y02T50/60
Abstract: A gas turbine engine having a rotor blade stage with a plurality of circumferentially spaced rotors, a nozzle stage adjacent the rotor blade stage and including an outer nozzle end, at least one stop, and a shroud. The shroud having a forward end positioned radially outward from the circumferentially spaced rotor blades, and an aft end axially aft of the forward end. The at least one stop confronting at least a portion of the outer nozzle end.
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公开(公告)号：US11898460B2
公开(公告)日：2024-02-13
申请号：US17836049
申请日：2022-06-09
Applicant: General Electric Company
Inventor： Jonathan Michael Rausch , Zachary Daniel Webster , Kevin Robert Feldmann , Andrew David Perry , Kirk Douglas Gallier , Daniel Endecott Osgood
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/30 , F05D2260/202
Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.
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公开(公告)号：US20230175405A1
公开(公告)日：2023-06-08
申请号：US17973976
申请日：2022-10-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Daniel Endecott Osgood , Kirk Douglas Gallier
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/307 , F05D2260/20
Abstract: An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.
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公开(公告)号：US11591966B2
公开(公告)日：2023-02-28
申请号：US17060162
申请日：2020-10-01
Applicant: General Electric Company
Abstract: Features and methods for modulating a flow of cooling fluid to gas turbine engine components are provided. In one embodiment, an airfoil is provided having a flow modulation insert for modulating a flow of cooling fluid received in a cavity of a body of the airfoil. In another embodiment, a shroud is provided comprising a cooling channel for a flow of cooling fluid and an insert that varies in position to modulate the flow of cooling fluid through the cooling channel. In yet another embodiment, a method for operating a gas turbine engine having a cooling circuit for cooling one or more components of the gas turbine engine comprises increasing power provided to the engine and decreasing power provided to the engine to modulate a position of a flow modulation insert located in the cooling circuit and thereby modulate the flow of cooling fluid through the cooling circuit.
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公开(公告)号：US11560803B1
公开(公告)日：2023-01-24
申请号：US17520146
申请日：2021-11-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Kirk Douglas Gallier , Zachary Daniel Webster , Gregory Terrence Garay , Daniel Lee Durstock , Ricardo Caraballo
Abstract: An engine component for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side. The engine component further comprising at least one cooling conduit provided in the interior and having conduit sidewalls and a set of cooling passages formed in the wall and fluidly coupling the at least one cooling conduit to the outer surface, at least one of the cooling passages in the set comprising a primary cooling passage portion and a secondary cooling passage portion. A diffusion slot located in the primary cooling passage portion and an impingement zone fluidly coupled to the diffusion slot.
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Patent Agency Ranking
公开(公告)号：US11486259B1
公开(公告)日：2022-11-01
申请号：US17519958
申请日：2021-11-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Kirk Douglas Gallier , Zachary Daniel Webster , Gregory Terrence Garay , Nicholas William Rathay , Daniel Lee Durstock
IPC: F01D5/18
Abstract: An engine component for a turbine engine comprising a wall defining an interior and having an outer surface over which flows the combustion airflow. The outer surface defining a first side and a second side extending between an upstream edge and a downstream edge and extending between a root and a tip. At least one cooling conduit provided in the interior and having conduit sidewalls; a set of cooling passages with at least one of the cooling passages in the set comprising: a first cooling passage portion having a surface outlet opening on the surface; a second cooling passage portion, intersecting the first cooling passage portion, and having an inlet fluidly coupled to the cooling conduit and an intermediate outlet fluidly connecting the second cooling passage portion to the first cooling passage at the intersection. The cooling passage comprising at least one fillet.
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公开(公告)号：US20220128236A1
公开(公告)日：2022-04-28
申请号：US17647235
申请日：2022-01-06
Applicant: General Electric Company
Inventor： Jinjie Shi , Robert Proctor , Jason Paul Hoppa , Stephen Gerard Schadewald , Christopher Edward Wolfe , Kirk Douglas Gallier
Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.
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公开(公告)号：US11306617B2
公开(公告)日：2022-04-19
申请号：US16593094
申请日：2019-10-04
Applicant: General Electric Company
Inventor： Kirk Douglas Gallier , Charles William Craig, III
Abstract: Shrouds and shroud segments for gas turbine engines are provided. In one embodiment, a shroud segment for a gas turbine engine having a rotor blade stage and a nozzle stage is provided. The shroud segment comprises a forward end defining an outer wall of the rotor blade stage and an aft end defining an outer wall of the nozzle stage. The aft end defines at least a portion of an opening therethrough for receipt of a nozzle, and the forward end and the aft end form a single, continuous component. In another embodiment, a gas turbine engine is provided, having a shroud with a forward end positioned near a leading edge of a plurality of rotor blades of a rotor blade stage and an aft end positioned near a trailing edge of a plurality of nozzles of a nozzle stage. Methods of assembling a gas turbine engine also are provided.
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公开(公告)号：US11021961B2
公开(公告)日：2021-06-01
申请号：US16210314
申请日：2018-12-05
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Kirk Douglas Gallier , Brandon Wayne Miller , Craig Alan Gonyou , Kevin Robert Feldmann , Justin Paul Smith
Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.
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公开(公告)号：US20210040859A1
公开(公告)日：2021-02-11
申请号：US16532787
申请日：2019-08-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Kirk Douglas Gallier , Daniel Lee Durstock , Zachary Daniel Webster , Gregory Terrence Garay
IPC: F01D5/18
Abstract: An apparatus and method for an engine component for a turbine engine comprising an outer wall having an outer surface and bounding an interior, the outer wall defining a pressure side and a suction side, extending axially between a leading edge and a trailing edge to define a chord-wise direction, and extending radially between a root and a tip to define a span-wise direction, at least one cooling supply conduit provided in the interior, and at least one cooling passage fluidly coupling the at least one cooling supply conduit to the outer surface of the outer wall, the at least one cooling passage comprising an outlet opening onto the outer surface along the leading edge, an inlet fluidly coupled to the at least one cooling supply conduit, and a curved passage defining a curvilinear centerline.
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