公开(公告)号：US12116903B2

公开(公告)日：2024-10-15

申请号：US17363102

申请日：2021-06-30

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas Joseph Kray ,  Daniel Edward Mollmann ,  David William Crall

IPC: F01D5/14 ,  F01D5/28 ,  F01D21/04

CPC classification number: F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F01D21/045 ,  F05D2220/36 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2300/6033

Abstract: Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.

公开(公告)号：US12044147B1

公开(公告)日：2024-07-23

申请号：US18176241

申请日：2023-02-28

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nitesh Jain ,  Nicholas J. Kray ,  Nuthi Srinivas

IPC: F01D5/28

CPC classification number: F01D5/288 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2300/611

Abstract: Examples disclosed herein include a fan blade of a gas turbine engine. The disclosed fan blade includes a main body having a leading edge and a trailing edge. The fan blade includes a leading edge guard covering the leading edge and a leading section of the main body adjacent to the leading edge. The leading edge guard includes a plurality of leading edge guard segments consecutively arranged in a spanwise direction along the leading edge of the fan blade. Each of the plurality of leading edge guard segments are oriented at an angle relative to a root of the fan blade. Each of the plurality of leading edge guard segments includes a nose portion coupled to the leading edge and a wing portion coupled to opposing sides of the leading section of the main body.

公开(公告)号：US20240229656A9

公开(公告)日：2024-07-11

申请号：US17970687

申请日：2022-10-21

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Nicholas M. Daggett ,  Nitesh Jain ,  Matthew Mark Weaver ,  Srinivas Addagatla

IPC: F01D7/00

CPC classification number: F01D7/00 ,  F05D2220/323 ,  F05D2240/30

Abstract: A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order. A fan defining a fan axis and comprising a plurality of fan blades is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.

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：US12018586B2

公开(公告)日：2024-06-25

申请号：US18081151

申请日：2022-12-14

Applicant: General Electric Company

Inventor： David Raju Yamarthi ,  Ravindra Shankar Ganiger ,  Vasanth Kumar Balaramudu ,  Vishnu Vardhan Venkata Tatiparthi ,  Nitesh Jain ,  Vidyashankar Ramasastry Buravalla

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F05D2230/60

Abstract: An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.

公开(公告)号：US11970956B2

公开(公告)日：2024-04-30

申请号：US18146511

申请日：2022-12-27

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Nitesh Jain ,  Ricardo Hernandez Pandeli

IPC: F01D7/00

CPC classification number: F01D7/00

Abstract: A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.

公开(公告)号：US11913355B2

公开(公告)日：2024-02-27

申请号：US17947589

申请日：2022-09-19

Applicant: General Electric Company

Inventor： Nicholas J. Kray ,  Nitesh Jain ,  Gary W. Bryant

IPC: F01D5/22 ,  F01D5/16

CPC classification number: F01D5/225 ,  F01D5/16

Abstract: Part-span shrouds for pitch controlled aircrafts are disclosed herein. An example apparatus includes a first portion extending from a first airfoil, the first portion including a first surface, the first surface being convex, a second portion extending from a second airfoil towards the first airfoil, the second portion including a second surface the first airfoil circumferentially adjacent to the second airfoil, the second surface being concave, and an interface formed by the first surface and the second surface, the interface reacting circumferential loads between the first airfoil and the second airfoil.

公开(公告)号：US20220298926A1

公开(公告)日：2022-09-22

申请号：US17207911

申请日：2021-03-22

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas Joseph Kray

IPC: F01D21/04

Abstract: Hybrid material components and methods of forming hybrid material components are provided. For example, a hybrid material component comprises a plurality of metallic tows and a plurality of non-metallic tows. Each metallic tow of the plurality of metallic tows is surrounded by a portion of the plurality of non-metallic tows such that the plurality of metallic tows are embedded within the plurality of non-metallic tows. An exemplary hybrid material component is a containment assembly of a gas turbine engine. Methods of forming such components include forming a hybrid material; laying up a plurality of layers of the material to form a layup; and processing the layup such that a plurality of metallic tows and a plurality of non-metallic tows are co-cured.

公开(公告)号：US11149558B2

公开(公告)日：2021-10-19

申请号：US16161200

申请日：2018-10-16

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas Joseph Kray ,  Kishore Budumuru

IPC: F01D5/28 ,  F01D21/04 ,  F02K3/06

Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span including a first plurality of composite plies. Each of the first plurality of composite plies includes fibers oriented at least partially along a chordwise direction, a thickness direction, or both. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span including a second plurality of composite plies. The second plurality of composite plies includes at least one composite ply with fibers oriented along the span. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.