公开(公告)号：US12031453B1

公开(公告)日：2024-07-09

申请号：US18104452

申请日：2023-02-01

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Nitesh Jain ,  Abhijeet Jayshingrao Yadav ,  Balaraju Suresh

IPC: F01D5/14 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2220/323 ,  F05D2230/23 ,  F05D2250/75 ,  F05D2300/603

Abstract: A component and blade assembly for a turbine engine, the component having a wall bounding an interior and defining an exterior surface extending radially between a leading edge and a trailing edge to define a chordwise direction, and between a hub and a tip to define a spanwise direction. A metallic spar extending from the hub in the spanwise direction into the interior, the metallic spar defining a socket. A composite spar extending in the spanwise direction between a spar root and a spar tip, the spar root received in the socket. The component further having a stiffener.

公开(公告)号：US20240209737A1

公开(公告)日：2024-06-27

申请号：US18104452

申请日：2023-02-01

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Nitesh Jain ,  Abhijeet Jayshingrao Yadav ,  Balaraju Suresh

IPC: F01D5/14 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2220/323 ,  F05D2230/23 ,  F05D2250/75 ,  F05D2300/603

Abstract: A component and blade assembly for a turbine engine, the component having a wall bounding an interior and defining an exterior surface extending radially between a leading edge and a trailing edge to define a chordwise direction, and between a hub and a tip to define a spanwise direction. A metallic spar extending from the hub in the spanwise direction into the interior, the metallic spar defining a socket. A composite spar extending in the spanwise direction between a spar root and a spar tip, the spar root received in the socket. The component further having a stiffener.

公开(公告)号：US11982205B1

公开(公告)日：2024-05-14

申请号：US18171490

申请日：2023-02-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nitesh Jain ,  Abhijeet Jayshingrao Yadav ,  Balaraju Suresh ,  Nicholas Joseph Kray

IPC: F01D5/14 ,  F01D5/28 ,  F01D9/02 ,  F01D9/04 ,  F01D25/24

CPC classification number: F01D5/147 ,  F01D5/282 ,  F01D9/02 ,  F01D9/04 ,  F01D9/041 ,  F01D9/042 ,  F01D25/243 ,  F01D25/246 ,  F05D2220/323 ,  F05D2300/603

Abstract: An airfoil for a turbine engine having a spar assembly. The spar assembly including a composite spar, a metallic hub, and a composite body. The metallic hub can receive a portion of the composite spar at an interior surface to define an overlapping region. The composite body is located at the overlapping region.

公开(公告)号：US20230407759A1

公开(公告)日：2023-12-21

申请号：US18046651

申请日：2022-10-14

Applicant: General Electric Company

Inventor： Illya Emmanuel Arcos Perez ,  Ashish Rajput ,  Amarnath Kakarla ,  Narayanan Payyoor ,  Abhijeet Yadav ,  Abhishek Goverdhan ,  Balaraju Suresh ,  Ricardo Hernandez Pandeli ,  Suryarghya Chakrabarti ,  Nicholas M. Daggett ,  Gary W. Bryant

IPC: F01D15/12 ,  B64D35/04 ,  F01D7/00

CPC classification number: F01D15/12 ,  B64D35/04 ,  F01D7/00 ,  F05D2260/70 ,  F05D2220/36

Abstract: An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.

公开(公告)号：US12281582B2

公开(公告)日：2025-04-22

申请号：US18046651

申请日：2022-10-14

Applicant: General Electric Company

Inventor： Illya Emmanuel Arcos Perez ,  Ashish Rajput ,  Amarnath Kakarla ,  Narayanan Payyoor ,  Abhijeet Yadav ,  Abhishek Goverdhan ,  Balaraju Suresh ,  Ricardo Hernandez Pandeli ,  Suryarghya Chakrabarti ,  Nicholas M. Daggett ,  Gary W. Bryant

IPC: F01D15/12 ,  B64D35/04 ,  F01D7/00

Abstract: An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.

公开(公告)号：US20250059894A1

公开(公告)日：2025-02-20

申请号：US18476474

申请日：2023-09-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Abhijeet Jayshingrao Yadav ,  Frank Worthoff ,  Nicholas Joseph Kray ,  Nitesh Jain ,  Balaraju Suresh

IPC: F01D5/28 ,  F02C7/00

Abstract: A turbine engine including a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The turbine engine further including a composite airfoil assembly. The composite airfoil assembly having an outer wall, a composite body at least partially defining the outer wall, and a tip cap at least partially defining the outer wall.

公开(公告)号：US20240376824A1

公开(公告)日：2024-11-14

申请号：US18314244

申请日：2023-05-09

Applicant: General Electric Company

Inventor： Balaraju Suresh ,  Guru Venkata Dattu Jonnalagadda ,  Trevor Howard Wood ,  Nicholas Joseph Kray ,  Vishnu Vardhan Venkata Tatiparthi ,  Nitesh Jain

IPC: F01D5/14

Abstract: An airfoil for a turbofan engine includes a first contoured sidewall, a second contoured sidewall, a leading edge, and a trailing edge with each extending in a spanwise direction defined between a root and a tip portion of the airfoil. The first contoured sidewall and the second contoured sidewall define an outer surface of the airfoil. The airfoil further includes a plurality of protrusions where each protrusion of the plurality of protrusions has a curvilinear shape and extends outwardly from the outer surface along at least one of the first contoured sidewall or the second contoured sidewall. The plurality of protrusions is defined downstream from a mid-point of a chord length of the airfoil and terminates upstream of the trailing edge.

公开(公告)号：US20240218797A1

公开(公告)日：2024-07-04

申请号：US18317310

申请日：2023-05-15

Applicant: General Electric Company

Inventor： Balaraju Suresh ,  Guru Venkata Dattu Jonnalagadda ,  Sandeep Kumar ,  Nitesh Jain ,  Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray

IPC: F01D5/28

CPC classification number: F01D5/28 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2300/17

Abstract: Methods of manufacturing airfoil assemblies include forming an airfoil core comprising a foam to define an airfoil shape extending in a first direction and having a pressure side and a suction side extending in a second direction, the second direction being perpendicular to the first direction, between a leading edge and a trailing edge; and electroforming a metal alloy onto an exterior surface of the airfoil core to define an external airfoil shell.