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.

公开(公告)号：US20230126549A1

公开(公告)日：2023-04-27

申请号：US17511850

申请日：2021-10-27

Applicant: General Electric Company

Inventor： Li Zheng ,  Nicholas Joseph Kray ,  Changjie Sun

IPC: F04D29/58 ,  F02C3/00

Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane, and an edge guard attached thereto. The edge guard may include a heating conduit disposed within at least a portion of the edge guard. An anti-icing system for a plurality of fan blades or outlet guide vanes may include a fluid supply pathway configured to supply heating fluid to respective ones of a plurality of heating conduits within the edge guards attached to respective ones of a plurality of fan blades and/or to a plurality of outlet guide vanes. The heating fluid may include bleed air from a core air flowpath. A method of inhibiting icing on an airfoil may include flowing a heating fluid into a heating conduit disposed within an edge guard attached to the airfoil and heating the edge guard with the heating fluid.

公开(公告)号：US11624320B2

公开(公告)日：2023-04-11

申请号：US17365855

申请日：2021-07-01

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Sreekanth Kumar Dorbala ,  Nitesh Jain ,  Prashant Sharma

IPC: F02C7/047 ,  B64D33/02 ,  F01D25/02

Abstract: A booster splitter for a gas turbine engine and a method of additively manufacturing the booster splitter are provided. The booster splitter includes an annular inner wall defining a radially outer boundary of a compressor flow path defined through a compressor section of the gas turbine engine, an annular outer wall spaced apart from the annular inner wall along the radial direction, the annular outer wall adjacent to the annular inner wall at a forward end, the forward end defining an inlet to the compressor flow path, an annular bulkhead spanning between the annular inner wall and the annular outer wall substantially along the radial direction, the bulkhead defining an inlet port, and a passageway defined within the annular outer wall, the passageway extending from the inlet port, into the bulkhead, radially outward to the outer wall, and through the annular outer wall towards the inlet defined by the forward end.

公开(公告)号：US20230020608A1

公开(公告)日：2023-01-19

申请号：US17375433

申请日：2021-07-14

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Raghuveer Chinta ,  Nicholas Joseph Kray ,  Wendy Wenling Lin

IPC: F01D5/28

Abstract: A fan platform for gas turbine engine is provided. The fan platform incudes a body portion and a flow path surface coupled to the body portion. The body portion and the flow path surface define at least a portion of a flow path extending through the engine. The body portion and/or the flow path surface include an impact region including hybrid composite plies including one or more metallic tows. A gas turbine engine including the fan platform and methods for forming the fan platform are also disclosed.