公开(公告)号：US20240280024A1

公开(公告)日：2024-08-22

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

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2220/36 ,  F05D2240/121 ,  F05D2240/303 ,  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：US12065943B2

公开(公告)日：2024-08-20

申请号：US17533566

申请日：2021-11-23

Applicant: General Electric Company

Inventor： Li Zheng ,  Nicholas Joseph Kray ,  Scott Roger Finn

IPC: F01D5/14 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2300/505 ,  F05D2300/603

Abstract: Morphable rotor blades for a turbine engine systems include a root portion and an airfoil portion having a morphable portion including a morphable material that changes shape in response to a stimulus.

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：US20230313687A1

公开(公告)日：2023-10-05

申请号：US17712701

申请日：2022-04-04

Applicant: General Electric Company

Inventor： Raghuveer Chinta ,  Srinivas Nuthi ,  Gary Willard Bryant, JR. ,  Nicholas Joseph Kray

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F05D2250/283 ,  F05D2230/50 ,  F05D2230/10 ,  F05D2300/612

Abstract: An airfoil assembly comprising a central spar extending along the radial direction; a blade skin positioned around the central spar to define an airfoil that has a pressure side and a suction side extending in the axial direction between a leading edge and a trailing edge, wherein at least one cavity is defined between the blade skin and the central spar; and a support structure positioned at least partially within the at least one cavity. The support structure comprises: a foam; and a foam reinforcement structure embedded within the foam.

公开(公告)号：US11773732B2

公开(公告)日：2023-10-03

申请号：US17236257

申请日：2021-04-21

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas Joseph Kray ,  Abhijeet Jayshingrao Yadav

IPC: F01D5/28 ,  F02C7/24 ,  F01D5/14

CPC classification number: F01D5/282 ,  F01D5/147 ,  F02C7/24 ,  F05D2240/30 ,  F05D2260/96 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/614

Abstract: A component for a turbine engine is provided. The component includes a main body portion having a flow path surface; and a protective layer formed of a chopped fiber material, the protective layer cohered to at least a portion of the flow path surface of the main body portion.

公开(公告)号：US20230304415A1

公开(公告)日：2023-09-28

申请号：US17702101

申请日：2022-03-23

Applicant: General Electric Company

Inventor： Li Zheng ,  Nicholas Joseph Kray ,  Changjie Sun

IPC: F01D11/22 ,  F01D11/12

CPC classification number: F01D11/22 ,  F01D11/122 ,  F05D2240/11 ,  F05D2260/232 ,  F05D2260/606 ,  F05D2300/505

Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine; a fan including a plurality of fan blades rotatably driven by the turbomachine; a nacelle surrounding at least in part the plurality of fan blades of the fan; and a clearance control system including a control ring positioned at least partially within the nacelle, coupled to the nacelle, or both for control of a clearance gap between the plurality of fan blades and the nacelle.

公开(公告)号：US11753942B1

公开(公告)日：2023-09-12

申请号：US17717272

申请日：2022-04-11

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Kirti Arvind Petkar ,  Viswanadha Gupta Sakala ,  Nicholas Joseph Kray

IPC: F01D21/04 ,  F01D5/14 ,  F04D29/32 ,  F01D5/28 ,  F01D5/16 ,  F01D5/10

CPC classification number: F01D5/147 ,  F01D5/10 ,  F01D5/16 ,  F01D5/28 ,  F01D21/045 ,  F04D29/324

Abstract: An airfoil for gas turbine engines is generally provided. The airfoil defines a span extending between a root and a tip, the airfoil further defines a chord at each point along the span extending between a leading edge and a trailing edge. Further, the airfoil includes at least one frangible airfoil portion, a residual airfoil portion adjacent to the at least one frangible airfoil portion, and one or more zones. The one or more zones may include a plurality of cavities, where at least one or more cavities of the plurality of cavities include inclusions, with the inclusions having one or more materials.

公开(公告)号：US11697996B2

公开(公告)日：2023-07-11

申请号：US17410739

申请日：2021-08-24

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Ian F. Prentice

IPC: F01D7/00 ,  F01D5/30 ,  F01D5/32 ,  B64C11/34 ,  B64C11/06

CPC classification number: F01D7/00 ,  F01D5/30 ,  F01D5/3007 ,  F01D5/3023 ,  F01D5/32 ,  B64C11/06 ,  B64C11/343 ,  F05B2260/74 ,  F05B2260/77 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2260/70 ,  F05D2260/74

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to adjust a pitch axis of a blade of an engine. An example blade apparatus includes: a hub to facilitate movement of blades in an engine, the engine having a radial center line; and a trunnion connected to the hub. The example trunnion includes a slot to accommodate a first blade, and at least one of the trunnion or the first blade is positioned with at least one of a tilt or a lean with respect to the radial center line to form a pitch axis offset from the radial center line such that the pitch axis is not parallel to or co-linear with the radial center line. The example hub is to rotate the first blade about the pitch axis.

公开(公告)号：US11674397B2

公开(公告)日：2023-06-13

申请号：US16950940

申请日：2020-11-18

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Naleen Kumar Verma ,  Nicholas Joseph Kray

IPC: F01D5/10 ,  F01D25/16

CPC classification number: F01D5/10 ,  F01D25/164 ,  F05D2240/50 ,  F05D2250/14 ,  F05D2260/96

Abstract: A variable stiffness damper system including an inner spring positioned between a first wall and a second wall, in which the inner spring includes a first member and a second member each coupled together at a distal end by an inner bumper. The first member and the second member are each contoured toward one another. The first member, the second member, and the inner bumper form a cavity therebetween. An outer spring is positioned between the inner spring and the first wall or the second wall. The outer spring includes a spring arm contoured toward the inner spring. The outer spring includes an outer bumper positioned between the inner bumper and the first wall or the second wall. The inner bumper and the outer bumper are selectively couplable to one another based on a load applied to the damper system.

公开(公告)号：US20230175407A1

公开(公告)日：2023-06-08

申请号：US17541859

申请日：2021-12-03

Applicant: General Electric Company

Inventor： Li Zheng ,  Nicholas Joseph Kray ,  Changjie Sun

IPC: F01D5/30 ,  F01D9/02 ,  F01D25/28

CPC classification number: F01D5/3007 ,  F01D9/02 ,  F01D25/28 ,  F05D2230/60 ,  F05D2220/32 ,  F05D2300/603

Abstract: A system for an outlet guide vane assembly and method of assembly thereof are provided herein. The outlet guide vane assembly generally includes a composite outlet guide vane that includes a monolithic body extending in an axial direction from a base to a top, as well as an anchor bracket. At least one of the base and the top includes a bulbous profile having a thickness in a radial direction that is greater than a thickness of the monolithic body in the radial direction, where the radial direction is orthogonal to the axial direction. The anchor bracket generally includes an anchor base, an engagement slot, and at least one side structure defining the engagement slot.