-
公开(公告)号：US20190205500A1
公开(公告)日：2019-07-04
申请号：US15861647
申请日：2018-01-03
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kevin Klasing , Eric Ruggiero , Daniel Endecott Osgood
CPC classification number: G06F17/5095 , F05D2220/32 , F05D2230/60 , G06Q10/06 , G06Q10/0635 , G06Q10/20 , G06Q50/04
Abstract: Systems, computer-implemented methods and/or computer program products that facilitate selecting components for aviation engines. In one embodiment, a computer-implemented method comprises: calculating, by a system operatively coupled to a processor, standard deviation between components for aviation engines based on a statistical distribution of measured manufacturing characteristics; selecting, by the system, a subset of components based on the calculated standard deviation; and analyzing, by the system, the subset of components at respective standard deviation to determine a standard deviation and period of time for trading that maximizes durability performance.
-
公开(公告)号：US20250027417A1
公开(公告)日：2025-01-23
申请号：US18440316
申请日：2024-02-13
Applicant: General Electric Company
Inventor： Jonathan Michael Rausch , Zachary Daniel Webster , Kevin Robert Feldmann , Andrew David Perry , Kirk Douglas Gallier , Daniel Endecott Osgood
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.
-
73.发明授权公开(公告)号：US12173897B2
公开(公告)日：2024-12-24
申请号：US17651743
申请日：2022-02-18
Applicant: General Electric Company
Inventor： Ryan Christopher Jones , Paul Christopher Schilling , Andrew Scott Bilse , Daniel Endecott Osgood , Donald Lee Gardner
Abstract: Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.
-
公开(公告)号：US20240383205A1
公开(公告)日：2024-11-21
申请号：US18442572
申请日：2024-02-15
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Bathrinarayanan Mukundan , Vaibhav Dabaria , Justin Michael Stekli , Xuefeng Zhang , Pinghai Yang
IPC: B29C64/386 , B33Y50/00
Abstract: A computer program product comprising a non-transitory computer-readable medium storing instructions, that when executed by a computer processor, cause the computer processor to discretize distinct surfaces of a 3D model defining nominal geometry of a component to be manufactured using an additive manufacturing machine; define a build orientation of the 3D model, the build orientation comprises an initial build plane and a build direction; apply one or more in-plane offsets to at least one of the discretized distinct surfaces of the 3D model; and generate an offset 3D model for use by the additive manufacturing machine to manufacture the component such that a manufactured component comprises the nominal geometry defined by the 3D model, where the offset 3D model defines the nominal geometry of the component offset by the one or more in-plane offsets applied to the at least one of the discretized distinct surfaces of the 3D model.
-
公开(公告)号：US20240337190A1
公开(公告)日：2024-10-10
申请号：US18295388
申请日：2023-04-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Susan Emily Schulz , Zachary Daniel Webster , Daniel Endecott Osgood , Jorge Rodrigo Quintero Badillo , Catherine Marie Rucki , Ricardo Caraballo , David Lawrence Holzschuh
CPC classification number: F01D5/188 , F01D5/147 , F05D2240/81 , F05D2260/201
Abstract: A turbine blade assembly for a turbine engine that generates a hot fluid flow and provides a cooling fluid flow. The turbine blade assembly having a platform with an upper wall radially spaced from a lower wall, and a platform wall connecting the upper wall to the lower wall to bound an interior of the platform. An airfoil extending from the upper wall and having an airfoil wall at least partially bounding an interior of the airfoil and defining a heated surface in contact with the hot fluid flow. At least one cooling supply conduit extending into the interior of the airfoil and multiple cores provided in the interior of the platform.
-
Patent Agency Ranking
公开(公告)号：US20240254885A1
公开(公告)日：2024-08-01
申请号：US18599470
申请日：2024-03-08
Applicant: General Electric Company
Inventor： Jonathan Michael Rausch , Zachary Daniel Webster , Kevin Robert Feldmann , Andrew David Perry , Kirk Douglas Gallier , Daniel Endecott Osgood
CPC classification number: F01D5/186 , F01D25/12 , F05D2220/32 , F05D2240/30 , F05D2260/202
Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (θ) with the heated surface.
-
公开(公告)号：US12042848B2
公开(公告)日：2024-07-23
申请号：US18079979
申请日：2022-12-13
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Evin Nathaniel Barber , Brian Patrick Peterson , Xi Yang , Christopher D. Barnhill , Brian David Przeslawski
Abstract: A casting assembly includes at least a first body and a second body. The first body can be a core and the second body can be a shell. The first body has a first interior surface and a first exterior surface. The second body has a second interior surface spaced from a second exterior surface. A portion of the second interior surface is spaced from and facing the first exterior surface. The first body having a casting hollow, where the casting hollow is at least partially defined by the first interior surface.
-
公开(公告)号：US20240141835A1
公开(公告)日：2024-05-02
申请号：US17978629
申请日：2022-11-01
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Jeffrey Donald Clements , Jeffrey S. Spruill , Daniel Endecott Osgood , Erich Alois Krammer , Matthew Kenneth MacDonald , Scott Alan Schimmels
CPC classification number: F02C9/16 , F02C7/18 , F05D2260/20 , F05D2270/303
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000).
-
公开(公告)号：US20240068370A1
公开(公告)日：2024-02-29
申请号：US17894307
申请日：2022-08-24
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/18 , F02C7/12 , F05D2260/20
Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.
-
公开(公告)号：US11905881B2
公开(公告)日：2024-02-20
申请号：US17410491
申请日：2021-08-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Jonathan Russell Ratzlaff , Kirk D. Gallier
CPC classification number: F02C7/052 , B01D45/16 , F01D9/041 , F01D25/12 , F01D25/32 , F02C7/18 , F05D2260/607
Abstract: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.
-
-
-
-
-
-
-
-
-
Search Results
96
records
(took 0.022 seconds)
