-
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.
-
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).
-
Patent Agency Ranking
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.
-
公开(公告)号：US11840941B2
公开(公告)日：2023-12-12
申请号：US17673084
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Lana Maria Osusky , Gustavo A. Ledezma , Daniel Endecott Osgood , Gregory Alexander Natsui
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/186 , F05D2200/11 , F05D2200/14 , F05D2200/212 , F05D2200/221 , F05D2260/20 , F05D2260/202 , F05D2260/2214
Abstract: An engine component for a gas turbine engine, the engine component comprising a cooling architecture comprising at least one unit cell having a set of walls with a thickness, the set of walls defining fluidly separate conduits having multiple openings, each of the multiple openings having a hydraulic diameter; wherein the thickness (t) and the hydraulic diameter (DH) relate to each other by an equation:
(
D
H
+
2
t
)
2
(
(
D
H
+
2
t
)
/
D
H
)
1
/
3
to define a performance area factor (PAF).-
公开(公告)号：US20230358139A1
公开(公告)日：2023-11-09
申请号：US18104371
申请日：2023-02-01
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/147 , F01D25/12 , F23C7/02 , F01D25/14 , F05D2300/70 , F05D2300/60
Abstract: A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.
-
公开(公告)号：US20230311199A1
公开(公告)日：2023-10-05
申请号：US17713540
申请日：2022-04-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Evin Nathaniel Barber , Joshua L. Miller , Christophe Jude Day , Brian D. Przeslawski , Tingfan Pang , Gregory Terrence Garay , Xi Yang , Meredith Elissa Dubelman , Daniel Endecott Osgood , Ricardo Caraballo , Thomas Hewitt
Abstract: An intermediate investment casting mold includes at least a shell and a core. The shell has an outer surface and an inner surface, with the inner surface defining an interior for the shell. The core is located in the interior of the shell and is at least partially spaced from the inner surface of the shell. A void can be defined as the space between the core and the inner surface. The intermediate investment casting mold can include a plurality of anchors.
-
-
-
-
-
-
-
-
-
Search Results
93
records
(took 0.034 seconds)
