公开(公告)号：US20240151147A1

公开(公告)日：2024-05-09

申请号：US17979853

申请日：2022-11-03

Applicant: General Electric Company

Inventor： Gary Willard Bryant, Jr. ,  Nicholas Joseph Kray ,  Ming Xie ,  Elzbieta Kryj-Kos ,  Douglas Lorrimer Armstrong ,  Nicholas M. Daggett ,  Frank Worthoff ,  Scott Roger Finn

IPC: F01D5/28

CPC classification number: F01D5/282 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2300/603

Abstract: The present disclosure relates to an airfoil assembly for a turbine engine and methods of assembly thereof. The airfoil assembly generally includes a composite airfoil and a spar. The composite airfoil has a pressure side and a suction side extending in an axial direction between a leading edge and a trailing edge defining a chordwise direction and extending radially between a root and a tip defining a spanwise direction and having a span-length. The spar includes a first portion including a first material and a second portion joined at an interface with the first portion. The second portion further includes a second material, different from the first material, joined to the first portion at an interface. The method generally includes joining the first portion with the second portion at the interface; and assembling the spar with the composite airfoil.

公开(公告)号：US20200291812A1

公开(公告)日：2020-09-17

申请号：US16891665

申请日：2020-06-03

Applicant: General Electric Company

Inventor： Frank Worthoff ,  Benjamin James Roby ,  Scott Roger Finn

IPC: F01D21/04 ,  F04D29/52 ,  F04D29/02

Abstract: An apparatus a multiple layer structure having a sub-portion defining an impact zone, and having an inner composite fiber layer, an outer composite fiber layer overlying the inner composite fiber layer, and a woven glass layer, where the inner composite fiber layer, outer composite fiber layer, and the woven glass layer overly the impact zone.

公开(公告)号：US20190136711A1

公开(公告)日：2019-05-09

申请号：US15805467

申请日：2017-11-07

Applicant: General Electric Company

Inventor： Frank Worthoff ,  Benjamin James Roby ,  Scott Roger Finn

IPC: F01D21/04 ,  F04D29/52 ,  F04D29/02

Abstract: An apparatus and method for a multiple layer fan casing surrounding a fan having a plurality of circumferentially spaced blades rotatable about a rotational axis and having a sub-portion defining a blade impact zone, the multiple layers comprising an inner fiber layer confronting the blades, an outer fiber layer overlying the inner carbon layer, a glass layer sandwiched between the inner and outer composite fiber layers.

公开(公告)号：US09797257B2

公开(公告)日：2017-10-24

申请号：US13709651

申请日：2012-12-10

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Scott Roger Finn ,  Peggy Lynn Baehmann ,  Joel Primmer White

IPC: F01D5/14 ,  F01D5/28 ,  B29D99/00 ,  B29C70/20 ,  B29C70/38 ,  B29L31/08

CPC classification number: F01D5/147 ,  B29C70/202 ,  B29C70/38 ,  B29D99/0025 ,  B29L2031/082 ,  F01D5/282 ,  Y02T50/672

Abstract: A composite article including composite component mounted on a spar including a shank extending heightwise from below component base up into composite component. Tab at an upper end of shank substantially or fully embedded in the composite component and at least one ply surface pattern of the composite component contacting and generally conforming to at least one spar surface pattern on the tab.Spar surface pattern may include spaced apart spar surface protrusions with spar surface spaces therebetween and spar surface protrusions extending outwardly from spar and disposed between tows in ply surface pattern. Tows may be layed up in spar surface spaces. Spar surface pattern may include continuous or segmented spaced spar surface protrusions and spar surface spaces therebetween with tows in ply surface pattern disposed in spar surface spaces. The composite article may be a composite blade or vane including a composite airfoil.

公开(公告)号：US11913346B2

公开(公告)日：2024-02-27

申请号：US16891665

申请日：2020-06-03

Applicant: General Electric Company

Inventor： Frank Worthoff ,  Benjamin James Roby ,  Scott Roger Finn

IPC: F01D21/04 ,  F04D29/52 ,  F04D29/02 ,  B32B5/12 ,  B32B5/26

CPC classification number: F01D21/045 ,  B32B5/12 ,  B32B5/263 ,  F04D29/023 ,  F04D29/526 ,  B32B2260/023 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/558 ,  B32B2605/18 ,  F05D2220/36 ,  F05D2230/50 ,  F05D2240/14 ,  F05D2300/2102 ,  F05D2300/603 ,  F05D2300/6012

Abstract: An apparatus a multiple layer structure having a sub-portion defining an impact zone, and having an inner composite fiber layer, an outer composite fiber layer overlying the inner composite fiber layer, and a woven glass layer, where the inner composite fiber layer, outer composite fiber layer, and the woven glass layer overly the impact zone.

公开(公告)号：US20230160312A1

公开(公告)日：2023-05-25

申请号：US17535291

申请日：2021-11-24

Applicant: General Electric Company

Inventor： Li Zheng ,  Scott Roger Finn ,  Nicholas J. Kray ,  Trevor H. Wood ,  Kishore Ramakrishnan

IPC: F01D5/30 ,  F01D5/28

CPC classification number: F01D5/3007 ,  F01D5/282 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2230/60

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement a low radius ratio fan blade for a gas turbine engine. A fan blade for a gas turbine engine includes an airfoil including a leading edge and a trailing edge extending between a root and a tip of the airfoil, a distance between the leading edge and the trailing edge defining a flow path length, a leading edge hub point defined by a radially innermost point of the leading edge, and an axial dovetail including a pair of opposed pressure faces, an axial length of the axial dovetail less than the flow path length, a top edge of the axial dovetail separating the pressure faces from the airfoil, the top edge of the axial dovetail radially outward of the leading edge hub point.

公开(公告)号：US11149584B2

公开(公告)日：2021-10-19

申请号：US16594208

申请日：2019-10-07

Applicant: General Electric Company

Inventor： David William Crall ,  Nicholas Joseph Kray ,  Scott Roger Finn ,  Wendy Wenling Lin

IPC: F01D21/04

Abstract: Containment assemblies and methods for forming containment assemblies of gas turbine engines are provided. For example, a containment assembly comprises a containment case including a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. As another example, a containment assembly comprises an inner case and a containment case comprising a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. The containment case includes a greater proportion of the coated fibers at an inner surface of a layer of the containment case than at a location within the containment case that is radially outward from the inner surface. Methods for forming a containment assembly of a gas turbine engine are provided.

公开(公告)号：US20210102475A1

公开(公告)日：2021-04-08

申请号：US16594208

申请日：2019-10-07

Applicant: General Electric Company

Inventor： David William Crall ,  Nicholas Joseph Kray ,  Scott Roger Finn ,  Wendy Wenling Lin

IPC: F01D25/26

Abstract: Containment assemblies and methods for forming containment assemblies of gas turbine engines are provided. For example, a containment assembly comprises a containment case including a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. As another example, a containment assembly comprises an inner case and a containment case comprising a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. The containment case includes a greater proportion of the coated fibers at an inner surface of a layer of the containment case than at a location within the containment case that is radially outward from the inner surface. Methods for forming a containment assembly of a gas turbine engine are provided.

公开(公告)号：US20180334922A1

公开(公告)日：2018-11-22

申请号：US15596523

申请日：2017-05-16

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Thomas Chadwick Waldman ,  Manoj Kumar Jain ,  Mojibur Rahman ,  Nitesh Jain ,  Nagamohan Govinahalli Prabhakar ,  Scott Roger Finn ,  Apostolos Pavlos Karafillis

IPC: F01D21/04 ,  F02C3/04 ,  F02K3/06 ,  F01D25/24

CPC classification number: F01D21/045 ,  F01D25/24 ,  F02C3/04 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2300/501

Abstract: A softwall containment system for a machine includes an inner wall circumscribing a bladed rotatable member of the machine and extending from a forward end to an aft end. The softwall containment system also includes an outer wall circumscribing the inner wall and extending from a forward end to an aft end. The outer wall is spaced radially outwardly from the inner wall. The outer wall extends axially between a first joint coupling the forward end of the inner wall to the forward end of the outer wall and a second joint coupling the aft end of the inner wall to the aft end of the outer wall. The softwall containment system also includes an anti-ballistic material wrap covering the outer wall, the anti-ballistic material wrap including at least one of a first extension extending forward of the first joint and a second extension extending aft of the second joint.

公开(公告)号：US09777579B2

公开(公告)日：2017-10-03

申请号：US13709559

申请日：2012-12-10

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Scott Roger Finn ,  Peggy Lynn Baehmann ,  Dong-Jin Shim ,  Gregory Carl Gemeinhardt

IPC: F01D5/14 ,  F01D5/28 ,  F01D5/30

CPC classification number: F01D5/141 ,  F01D5/282 ,  F01D5/30 ,  F05D2300/603 ,  Y02T50/672 ,  Y10T428/24017 ,  Y10T428/24182

Abstract: A composite article including composite component extending heightwise from a component base to a component tip and lengthwise between spaced apart component first and second edges. Component plies having widthwise spaced apart ply first and second sides and ply edges therebetween. Component mounted on a spar which includes a shank extending heightwise into the composite component, tab at upper end of shank and substantially or fully embedded in the composite component, and tab tip. Ply edges of at least a first portion of the plies directly or indirectly contacting or pressing against the tab. Ply edges of at least a second portion of the plies may directly or indirectly contact or press against the tab tip. Ply edges of first portion may press against one or more indented or recessed surfaces in the tab. The composite article may be a composite blade or vane including a composite airfoil.