公开(公告)号：US12055065B1

公开(公告)日：2024-08-06

申请号：US18536535

申请日：2023-12-12

Applicant: General Electric Company

Inventor： Vamshi Krishna Reddy Kommareddy ,  Nuthi Srinivas ,  Guru Venkata Dattu Jonnalagadda ,  Sandeep Kumar

IPC: F01D5/14 ,  F01D5/28 ,  F01D9/02 ,  F01D25/00

CPC classification number: F01D5/147 ,  F01D5/282 ,  F01D9/02 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2300/17 ,  F05D2300/603

Abstract: An airfoil for a gas turbine engine includes an exterior skin layer having a pressure side surface, a suction side surface, a leading edge, and a trailing edge. The exterior skin layer defines an interior volume. The airfoil further includes a primary structure within the interior volume between the pressure and suction side surfaces. The primary structure includes one or more primary meta-structures. The airfoil further includes a secondary structure within the interior volume adjacent to the primary structure between the pressure and suction side surfaces. The secondary structure includes at least one isogrid structure. Further, one or more of the plurality of primary meta-structures of the primary structure is connected to at least a portion of the at least one isogrid structure of the secondary structure.

公开(公告)号：US12241375B2

公开(公告)日：2025-03-04

申请号：US18189379

申请日：2023-03-24

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  David Raju Yamarthi ,  Chandrashekhar Kandukuri ,  Deepak Trivedi ,  Narendra Anand Hardikar ,  Vidyashankar Ramasastry Buravalla ,  Steven Douglas Johnson ,  Amit Goyal ,  Grant Robert Portune ,  Himanshu Gupta ,  Srinivasan Swaminathan ,  Shalini Thimmegowda ,  Guru Venkata Dattu Jonnalagadda ,  Shalabh Saxena ,  Prateek Jalan

IPC: F01D11/02

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

公开(公告)号：US20250163599A1

公开(公告)日：2025-05-22

申请号：US18542881

申请日：2023-12-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Srinivasan Swaminathan ,  Shalini Thimmegowda ,  Chirayu Pradip Inamdar ,  Guru Venkata Dattu Jonnalagadda ,  Udaya Bhaskar Pamidimarri

IPC: C25D3/12 ,  C25D7/00

Abstract: An electroforming system and method includes disposing a cathode defining a mandrel within an electrolytic solution, and applying a voltage to the cathode in the electrolytic solution to form a coating on the cathode. The coating can be formed as an amorphous coating, having no discernible grain boundaries or no discernible long-range order.

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：US20240318570A1

公开(公告)日：2024-09-26

申请号：US18189379

申请日：2023-03-24

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  David Raju Yamarthi ,  Chandrashekhar Kandukuri ,  Deepak Trivedi ,  Narendra Anand Hardikar ,  Vidyashankar Ramasastry Buravalla ,  Steven Douglas Johnson ,  Amit Goyal ,  Grant Robert Portune ,  Himanshu Gupta ,  Srinivasan Swaminathan ,  Shalini Thimmegowda ,  Guru Venkata Dattu Jonnalagadda ,  Shalabh Saxena ,  Prateek Jalan

IPC: F01D11/02

CPC classification number: F01D11/025 ,  F05D2240/53 ,  F05D2240/55 ,  F05D2260/38

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

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.