公开(公告)号：US12121956B1

公开(公告)日：2024-10-22

申请号：US18321216

申请日：2023-05-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Evin Nathaniel Barber ,  Brian Patrick Peterson ,  Xi Yang ,  Brian D. Przeslawski ,  Christopher D. Barnhill ,  Douglas G. Konitzer

IPC: B22C9/10 ,  B22C9/24

CPC classification number: B22C9/10 ,  B22C9/24

Abstract: A casting assembly includes a core body extending along an axial direction between a first end and a second end, the core body having a core interior surface and a core exterior surface, with the core exterior surface shaping a part surface of a cast part. The core interior surface at least partially bounds a hollow cavity. The casting assembly also includes a shell body extending along the axial direction and having a first shell surface and a second shell surface, with at least a portion of the second shell surface facing the exterior surface of the core body.

公开(公告)号：US20240254922A1

公开(公告)日：2024-08-01

申请号：US18500517

申请日：2023-11-02

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

IPC: F02C7/18 ,  F02C3/113 ,  F02C6/06 ,  F02C6/20 ,  F02K3/065 ,  F02K3/115

CPC classification number: F02C7/185 ,  F02C3/113 ,  F02C6/06 ,  F02C6/206 ,  F02K3/065 ,  F02K3/115 ,  F05D2260/213

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：US20240175364A1

公开(公告)日：2024-05-30

申请号：US18432818

申请日：2024-02-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Gregory Terrence Garay ,  Ryan Christopher Jones ,  Tingfan Pang

IPC: F01D5/14 ,  F01D25/12 ,  F01D25/14 ,  F23C7/02

CPC classification number: F01D5/147 ,  F01D25/12 ,  F01D25/14 ,  F23C7/02 ,  F05D2300/60 ,  F05D2300/70

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：US11988109B2

公开(公告)日：2024-05-21

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 ,  F01D5/08

CPC classification number: F01D5/187 ,  F01D5/087 ,  F05D2240/307 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/232

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.

公开(公告)号：US11879356B2

公开(公告)日：2024-01-23

申请号：US17852875

申请日：2022-06-29

Applicant: General Electric Company

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Kevin Robert Feldmann

IPC: F01D5/18 ,  F01D5/14 ,  F01D11/12 ,  F01D5/28 ,  F01D1/12 ,  F01D11/14

CPC classification number: F01D5/186 ,  F01D1/12 ,  F01D5/147 ,  F01D5/284 ,  F01D11/122 ,  F01D11/14 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/311 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2300/514

Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

公开(公告)号：US20230399953A1

公开(公告)日：2023-12-14

申请号：US17836023

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 ,  F01D25/12

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：US11420259B2

公开(公告)日：2022-08-23

申请号：US16675384

申请日：2019-11-06

Applicant: General Electric Company

Inventor： Daniel Endecott Osgood ,  Daniel Peter Kiefer

IPC: B22F10/00 ,  B33Y10/00 ,  B33Y80/00 ,  B33Y50/02 ,  H04L9/08 ,  G06F7/58 ,  B22F10/10

Abstract: A method of forming a mated component pair includes forming a first geometry on a first mating surface of a first component and a complementary second geometry on a second mating surface of a second component. The first geometry and the second geometry can be determined from a geometric key associated with a component identifier, e.g., by inputting the geometric key into a mathematical algorithm or random number generator. When a replacement for the second component is needed, the component identifier may be obtained from the first component, the component identifier may be used to obtain the geometric key, and the geometric key may then be used to determine the second geometry. The second geometry may then be formed on the second component such the second component may properly mate with the mated first component.

公开(公告)号：US11174736B2

公开(公告)日：2021-11-16

申请号：US16224065

申请日：2018-12-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Tingfan Pang ,  Kirk D. Gallier

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/30 ,  B22F10/20 ,  B33Y10/00 ,  B33Y80/00 ,  B22F10/30

Abstract: Aspects generally relate to a method of forming a plexus within an additively-manufactured component. The method includes forming a fluid passage in the plexus by serially forming layers of material along a build direction to form a column defining the fluid passage along a first direction within an interior of a turbine engine component.

公开(公告)号：US20210220904A1

公开(公告)日：2021-07-22

申请号：US17221911

申请日：2021-04-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Tingfan Pang ,  Gregory Terrence Garay ,  Zachary Daniel Webster ,  Ryan Christopher Jones

IPC: B22C9/10 ,  B22C9/12 ,  B22C9/26 ,  B22C7/02 ,  B22C21/14 ,  F01D5/18 ,  B28B7/34 ,  B28B1/00

Abstract: A leachable casting core and method of manufacture may include a plurality of legs configured to establish a plurality of internal flow channels of a cast component. Tie bars, with a first tie bar end and a second tie bar end opposite thereof, may couple to at least two of the plurality of legs. At least one of the tie bars may be oriented to form a linking cavity within the cast component between the internal flow channels. The linking cavity may serve as an obstruction to fluid communication through the linking cavity.

公开(公告)号：US20210148242A1

公开(公告)日：2021-05-20

申请号：US17158670

申请日：2021-01-26

Applicant: General Electric Company

Inventor： Ryan Christopher Jones ,  Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Tingfan Pang

IPC: F01D11/00 ,  F01D9/04

Abstract: A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.