公开(公告)号：US20240280028A1

公开(公告)日：2024-08-22

申请号：US18171836

申请日：2023-02-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Clive Andrew Morgan ,  Zachary Allen Hase ,  Brian Lee DeVilbiss ,  Daniel Endecott Osgood

IPC: F01D5/30 ,  F02C3/04

CPC classification number: F01D5/3007 ,  F02C3/04

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 set of blades are circumferentially arranged in the turbine section and the compressor section. A set of dovetails mounts the set of blades to a disk, rotated about the engine centerline. Each dovetail can include a set of lobes defining complementary recesses, collectively defining a neck for mounting to the disk.

公开(公告)号：US11952912B2

公开(公告)日：2024-04-09

申请号：US17894307

申请日：2022-08-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Thomas William Vandeputte ,  Paul Hadley Vitt ,  Daniel Endecott Osgood ,  Brian David Keith

IPC: F01D5/18 ,  F02C7/12

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：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.

公开(公告)号：US20230393554A1

公开(公告)日：2023-12-07

申请号：US18453746

申请日：2023-08-22

Applicant: General Electric Company

Inventor： Daniel Endecott Osgood ,  Tingfan Pang ,  Gregory Terrence Garay ,  Xi Yang ,  Daniel Lee Durstock ,  Steven Robert Brassfield ,  William Charles Herman

IPC: G05B19/4099 ,  B29C64/393 ,  G06F30/10

CPC classification number: G05B19/4099 ,  B29C64/393 ,  G06F30/10 ,  G05B2219/35036 ,  G05B2219/35134 ,  G05B2219/49007

Abstract: A method of forming a component that includes identifying an acute angle in an original model that is a virtual model of the component. The acute angle is defined by a first surface and a second surface. The method includes compensating the original model at the acute angle to create a compensated acute angle in a compensated model. The method also includes forming, by additive manufacturing, the component based upon the compensated model, where the formed component is more alike the original model than the compensated model.

公开(公告)号：US20230323813A1

公开(公告)日：2023-10-12

申请号：US17716712

申请日：2022-04-08

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Lana Maria Osusky ,  Daniel Endecott Osgood

IPC: F02C7/12 ,  F28D1/02 ,  F28D1/053 ,  F28D7/16 ,  F28D21/00 ,  F28F1/00 ,  F28F13/12

CPC classification number: F02C7/12 ,  F28D1/0233 ,  F28D1/05375 ,  F28D7/163 ,  F28D21/00 ,  F28F1/006 ,  F28F13/12 ,  F28D2021/0021 ,  F28D2021/004 ,  F28F2009/226

Abstract: An heat exchanger and method for forming the heat exchanger, the heat exchanger including 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 an average fluid temperature (Tf) to material temperature limit (Tm) ratio (Tf/Tm) is greater than 0 and less than or equal to 1.25 (0

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.

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

IPC: F01D5/18 ,  F01D5/08

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.

公开(公告)号：US11499431B2

公开(公告)日：2022-11-15

申请号：US17142788

申请日：2021-01-06

Applicant: General Electric Company

Inventor： Gregory Terrence Garay ,  Daniel Endecott Osgood ,  Douglas Gerard Konitzer

IPC: F01D5/14 ,  G06F30/17 ,  G06F113/06

Abstract: An apparatus and method for forming an engine component for a turbine engine, the engine component comprising a wall bounding an interior; a panel portion defining a portion of the wall, the panel portion comprising: an outer wall; an inner wall spaced from the outer wall to define a wall gap; and a structural segment formed within the wall gap comprising at least one structural element. The method including calculating a factor and adjusting a variable until the factor is between a given range.

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.

公开(公告)号：US11236618B2

公开(公告)日：2022-02-01

申请号：US17082288

申请日：2020-10-28

Applicant: General Electric Company

Inventor： Tingfan Pang ,  Helen Ogbazion Gabregiorgish ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Steven Robert Brassfield ,  Daniel Endecott Osgood

IPC: F01D5/18

Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. A plurality of outlets and a plurality of scalloped portions can extend along the outer wall.