公开(公告)号：US20240287906A1

公开(公告)日：2024-08-29

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: F01D5/14 ,  F01D5/28 ,  F01D9/04

CPC classification number: F01D5/147 ,  F01D5/282 ,  F01D5/323 ,  F01D5/326 ,  F01D9/041 ,  F01D11/008

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：US20240401482A1

公开(公告)日：2024-12-05

申请号：US18327172

申请日：2023-06-01

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph KRAY ,  Tod Winton DAVIS ,  Gary Willard BRYANT, JR.

IPC: F01D5/14

Abstract: A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil having opposite pressure and suction sides and opposite leading and trailing edges. The pressure side and the suction side extend axially between the leading edge and the trailing edge. The composite airfoil has a laminate skin that is applied to at least a portion of a core. A first cladding and a second cladding, having adjacent segments, are located on the pressure side or the suction side of the composite airfoil.