-
公开(公告)号：US20240392688A1
公开(公告)日：2024-11-28
申请号：US18792941
申请日：2024-08-02
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
-
公开(公告)号：US20240384657A1
公开(公告)日：2024-11-21
申请号：US18318950
申请日：2023-05-17
Inventor： Nicholas Joseph Kray , Nicholas Mark Daggett , Elzbieta Kryj-Kos , Necip Adali , Benjamin Thomas Van Oflen , Gary Willard Bryant, JR. , Douglas Lorrimer Armstrong
IPC: F01D5/14
Abstract: A turbine engine including a fan section, a compressor section, a combustion section, a turbine section, and an airfoil assembly. The airfoil assembly comprising a spar, a trunnion and a stress relief. The trunnion having an upper edge with an open top, and a socket extending from the open top. The spar extending through the open top and into the socket. A junction being formed between the spar and a portion of the upper edge defining the open top.
-
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：US20240271539A1
公开(公告)日：2024-08-15
申请号：US18644467
申请日：2024-04-24
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：US12037938B1
公开(公告)日：2024-07-16
申请号：US18345002
申请日：2023-06-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray
Abstract: A composite airfoil assembly for a turbine engine. The composite airfoil assembly has an airfoil outer surface defining opposing pressure and suction sides, which extend between a leading edge and a trailing edge. The composite airfoil assembly includes a composite airfoil having a woven core and a skin applied to at least a portion of a core exterior. The composite airfoil assembly also includes a cladding coupled to a skin outer surface where at least one edge or portion of the cladding is located adjacent at least one of the trailing edge, a root, or a tip, wherein the cladding includes a tapered portion.
-
Patent Agency Ranking
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.
-
公开(公告)号：US20240209742A1
公开(公告)日：2024-06-27
申请号：US18088990
申请日：2022-12-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Michael John Franks
CPC classification number: F01D5/282 , F01D5/147 , F01D5/30 , F05D2300/6034
Abstract: A composite blade assembly for a turbine engine, the composite blade assembly having a core and a laminate skin. The core having a composite structure. The laminate skin having at least one composite ply. The laminate skin having a first portion forming a first angle relative to a horizontal plane, and a second portion forming a second angle relative to the horizontal plane.
-
公开(公告)号：US20240209741A1
公开(公告)日：2024-06-27
申请号：US18088957
申请日：2022-12-27
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/282 , F01D5/147 , F01D5/3007 , F05D2220/32 , F05D2240/24 , F05D2240/30 , F05D2300/603
Abstract: A composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.
-
公开(公告)号：US20240133301A1
公开(公告)日：2024-04-25
申请号：US17970687
申请日：2022-10-20
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：US11898464B2
公开(公告)日：2024-02-13
申请号：US17232822
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain
CPC classification number: F01D5/282 , F01D5/147 , F05D2220/36 , F05D2300/603
Abstract: In one exemplary embodiment of the present disclosure an airfoil is provided. The airfoil defines a spanwise direction, a root end, and a tip end. The airfoil includes: a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction.
-
-
-
-
-
-
-
-
-
Search Results
286
records
(took 0.03 seconds)
