公开(公告)号：US20240110521A1

公开(公告)日：2024-04-04

申请号：US17958536

申请日：2022-10-03

Applicant: General Electric Company

Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

IPC: F02C7/24 ,  F01D11/08 ,  F02C3/06

CPC classification number: F02C7/24 ,  F01D11/08 ,  F02C3/06 ,  F05D2240/14 ,  F05D2250/184 ,  F05D2260/96

Abstract: A rotary component includes a plurality of rotor blades operably coupled to a rotating shaft extending along a central axis of the rotary component and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the rotary component. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Further, at least one feature of the plurality of features is a slot having an acoustic liner feature integrated therein to reduce operational noise of the rotary component.

公开(公告)号：US11802525B2

公开(公告)日：2023-10-31

申请号：US17647425

申请日：2022-01-07

Applicant: General Electric Company

Inventor： Vinod Chaudhari ,  Bhaskar Nanda Mondal ,  Kishanjit Pal ,  Sushilkumar Shevakari ,  Ian F. Prentice ,  Thomas Moniz ,  Trevor H. Wood ,  Kishore Ramakrishnan

IPC: F04D29/36 ,  F02K5/00 ,  F04D19/00

CPC classification number: F02K5/00 ,  F04D19/002 ,  F04D29/36

Abstract: An unducted single fan engine includes a housing having one or more fan blades coupled to the housing and configured to rotate circumferentially. The engine has one or more outlet guide vanes coupled to the housing. Each of the one or more guide vanes has a leading edge portion having a variable leading edge. The engine has one or more actuation devices coupled to each of the one or more outlet guide vanes. The one or more actuation devices are configured to control the variable leading edge of the respective outlet guide vane. The variable leading edge is controllable to vary the pitch, camber, lean angle, or sweep of the respective outlet guide vane.

公开(公告)号：US11759861B2

公开(公告)日：2023-09-19

申请号：US17232467

申请日：2021-04-16

Applicant: General Electric Company ,  Concept Laser GmbH

Inventor： Eric Edward Halla ,  Ramakrishna Venkata Mallina ,  Kishore Ramakrishnan ,  Shashwat Swami Jaiswal ,  Mohammed Mounir Shalaby ,  Adam Garret Susong ,  Peter Pontiller-Schymura

IPC: B33Y30/00 ,  B22F10/28 ,  B33Y10/00 ,  B22F12/41 ,  B22F12/70

CPC classification number: B22F10/28 ,  B22F12/41 ,  B22F12/70 ,  B33Y10/00 ,  B33Y30/00 ,  B22F2201/10

Abstract: A build unit for additively manufacturing three-dimensional objects may include an energy beam system having one or more irradiation devices respectively configured to direct one or more energy beams onto a region of a powder bed, and an inertization system including an irradiation chamber defining an irradiation plenum, one or more supply manifolds, and a return manifold. The one or more supply manifolds may include a downflow manifold configured to provide a downward flow of a process gas through at least a portion of the irradiation plenum defined by the irradiation chamber, and/or a crossflow manifold configured to provide a lateral flow of the process gas through at least a portion of the irradiation plenum defined by the irradiation chamber. The return manifold may evacuate or otherwise remove process gas from the irradiation plenum defined by the irradiation chamber.

公开(公告)号：US20230220816A1

公开(公告)日：2023-07-13

申请号：US17647425

申请日：2022-01-07

Applicant: General Electric Company

Inventor： Vinod Chaudhari ,  Bhaskar Nanda Mondal ,  Kishanjit Pal ,  Sushilkumar Shevakari ,  Ian F. Prentice ,  Thomas Moniz ,  Trevor H. Wood ,  Kishore Ramakrishnan

IPC: F02K5/00 ,  F04D19/00 ,  F04D29/36

CPC classification number: F02K5/00 ,  F04D19/002 ,  F04D29/36

Abstract: An unducted single fan engine includes a housing having one or more fan blades coupled to the housing and configured to rotate circumferentially. The engine has one or more outlet guide vanes coupled to the housing. Each of the one or more guide vanes has a leading edge portion having a variable leading edge. The engine has one or more actuation devices coupled to each of the one or more outlet guide vanes. The one or more actuation devices are configured to control the variable leading edge of the respective outlet guide vane. The variable leading edge is controllable to vary the pitch, camber, lean angle, or sweep of the respective outlet guide vane.

公开(公告)号：US11299283B2

公开(公告)日：2022-04-12

申请号：US16512730

申请日：2019-07-16

Applicant: General Electric Company

Inventor： Kishore Ramakrishnan ,  Jixian Yao ,  Nikolai N. Pastouchenko ,  Ivan Malcevic

IPC: B64D27/14 ,  B64C21/00 ,  B64D27/20 ,  B64C5/06 ,  B64C1/16 ,  B64C21/08 ,  B64C1/00

Abstract: An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The fuselage defines a profile proximate the boundary layer ingestion fan that is optimized for ingesting a maximum amount of boundary layer air and improving propulsive efficiency of the aircraft. More specifically, the fuselage defines a cross sectional profile upstream of the boundary layer ingestion fan that has more cross sectional area in a top half relative to a bottom half as defined relative to a centerline of the boundary layer ingestion fan.

公开(公告)号：US20210269144A1

公开(公告)日：2021-09-02

申请号：US17325592

申请日：2021-05-20

Applicant: General Electric Company

Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

IPC: B64C23/06

Abstract: An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.

公开(公告)号：US11034436B2

公开(公告)日：2021-06-15

申请号：US16033583

申请日：2018-07-12

Applicant: General Electric Company

Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

IPC: B64C23/06

Abstract: An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.

公开(公告)号：US20210107631A1

公开(公告)日：2021-04-15

申请号：US16987934

申请日：2020-08-07

Applicant: General Electric Company

Inventor： Kishore Ramakrishnan ,  Trevor Howard Wood

IPC: B64C21/06 ,  B64D27/20 ,  B64D33/02 ,  B64C7/02 ,  B64D27/24 ,  B64D29/04

Abstract: An aircraft defines a longitudinal direction and includes a fuselage extending between a forward end and an aft end along the longitudinal direction of the aircraft. An aft engine is mounted to the aft end of the fuselage. The aft engine further includes a nacelle including a forward section. An airflow duct extends at least partially through the nacelle of the aft engine and defines an outlet on the forward section of the nacelle for providing an airflow to the forward section of the nacelle.

公开(公告)号：US10704418B2

公开(公告)日：2020-07-07

申请号：US16377736

申请日：2019-04-08

Applicant: General Electric Company

Inventor： Kishore Ramakrishnan ,  Shourya Prakash Otta

IPC: B64D33/02 ,  F01D25/24 ,  B64D29/00 ,  B64D27/12 ,  B64C30/00

Abstract: An engine for mounting in or to an aircraft includes a stage of compression airfoils rotatable about a central axis; a casing surrounding the stage of compression airfoils and defining an inlet; and a low-distortion inlet assembly mounted within the inlet. The inlet assembly includes one or more structural members mounted at predetermined locations around a circumference of the central axis within the inlet, the predetermined locations defining an airflow distortion exceeding a predetermined threshold; and at least one airflow modifying element configured within the inlet so as to reduce airflow distortion entering the stage of compression airfoils.

公开(公告)号：US20200017200A1

公开(公告)日：2020-01-16

申请号：US16033583

申请日：2018-07-12

Applicant: General Electric Company

Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

IPC: B64C23/06

Abstract: An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.