公开(公告)号：US12241383B2

公开(公告)日：2025-03-04

申请号：US18173952

申请日：2023-02-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Benjamin Thomas Van Oflen ,  Gary Willard Bryant, Jr. ,  Nicholas Joseph Kray ,  Arthur William Sibbach ,  Michael John Franks ,  Elzbieta Kryj-Kos

IPC: F01D11/00 ,  F01D5/14 ,  F01D5/26 ,  F01D5/28 ,  F01D5/32 ,  F01D9/04

Abstract: A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.

公开(公告)号：US20250052166A1

公开(公告)日：2025-02-13

申请号：US18806969

申请日：2024-08-16

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

IPC: F01D9/04 ,  F01D5/14

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：US12173658B2

公开(公告)日：2024-12-24

申请号：US18085714

申请日：2022-12-21

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  John Carl Glessner ,  Lawrence William Nurre ,  Ian Francis Prentice ,  Ethan Patrick O'Connor ,  Arthur William Sibbach

IPC: F02C7/32 ,  F01D25/24 ,  F02C3/06

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

公开(公告)号：US20240410285A1

公开(公告)日：2024-12-12

申请号：US18807233

申请日：2024-08-16

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

IPC: F01D5/28 ,  F02C3/06

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：US12158082B2

公开(公告)日：2024-12-03

申请号：US18171533

申请日：2023-02-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

IPC: F01D5/14 ,  F01D5/28

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：US20240392689A1

公开(公告)日：2024-11-28

申请号：US18792961

申请日：2024-08-02

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

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

Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. 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：US20240352862A1

公开(公告)日：2024-10-24

申请号：US18304784

申请日：2023-04-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Tod Winton Davis ,  Nicholas Mark Daggett ,  Arthur William Sibbach ,  Elzbieta Kryj-Kos

IPC: F01D5/30 ,  F01D5/28 ,  F01D5/32

CPC classification number: F01D5/3023 ,  F01D5/282 ,  F01D5/32 ,  F05D2260/37 ,  F05D2300/603

Abstract: An airfoil assembly having a trunnion and a spar. The trunnion having an interior surface defining a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar further having a furcated tail with a set of branches defining an intervening gap between adjacent branches of the set of branches

公开(公告)号：US20240328431A1

公开(公告)日：2024-10-03

申请号：US18741419

申请日：2024-06-12

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

IPC: F04D29/38 ,  F02K3/06

CPC classification number: F04D29/388 ,  F02K3/06 ,  F05D2220/36 ,  F05D2300/603

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：US12104499B2

公开(公告)日：2024-10-01

申请号：US18330000

申请日：2023-06-06

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Daniel Alan Niergarth ,  Arthur William Sibbach ,  Brandon Wayne Miller

IPC: F02C7/12 ,  F01D25/10 ,  F01D25/12

CPC classification number: F01D25/10 ,  F01D25/12 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213

Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.

公开(公告)号：US12085019B2

公开(公告)日：2024-09-10

申请号：US18455137

申请日：2023-08-24

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Brandon Wayne Miller

IPC: F02K3/00 ,  F02C6/20 ,  F02C7/04 ,  F02C7/05

CPC classification number: F02C7/05 ,  F02C6/20 ,  F02C7/04 ,  F02K3/00 ,  F05D2220/36

Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.