公开(公告)号：US11549391B2

公开(公告)日：2023-01-10

申请号：US17207911

申请日：2021-03-22

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas Joseph Kray

IPC: F01D21/04

Abstract: Hybrid material components and methods of forming hybrid material components are provided. For example, a hybrid material component comprises a plurality of metallic tows and a plurality of non-metallic tows. Each metallic tow of the plurality of metallic tows is surrounded by a portion of the plurality of non-metallic tows such that the plurality of metallic tows are embedded within the plurality of non-metallic tows. An exemplary hybrid material component is a containment assembly of a gas turbine engine. Methods of forming such components include forming a hybrid material; laying up a plurality of layers of the material to form a layup; and processing the layup such that a plurality of metallic tows and a plurality of non-metallic tows are co-cured.

公开(公告)号：US20220403741A1

公开(公告)日：2022-12-22

申请号：US17891312

申请日：2022-08-19

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain

IPC: F01D5/02

Abstract: A rotor blade for a gas turbine engine includes an airfoil section and a root section extending along a longitudinal direction between an upstream surface and a downstream surface. The root section further extends along a radial direction between an inner surface positioned at an inner end of the root section and an outer end coupled to the airfoil section. Moreover, the root section extends along a circumferential direction between a first side surface and a second side surface. Furthermore, the root section defines a longitudinal centerline extending along the longitudinal direction and positioned equidistant from the inner surface and the outer end in the radial direction. The root section includes a first portion formed from a composite material and a second portion formed from a metallic material, with the longitudinal centerline extending through the second portion of the root section.

公开(公告)号：US11365636B2

公开(公告)日：2022-06-21

申请号：US16923911

申请日：2020-07-08

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Viswanadha Gupta Sakala ,  Nicholas Joseph Kray ,  Ambika Shivamurthy ,  Kirti Arvind Petkar

IPC: F01D5/02 ,  F01D5/14 ,  G06F30/17

Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure coupled to the first side of the exterior body and the second side of the exterior body; and a second hairpin structure coupled to the first side and the second side, the first hairpin structure in contact with the second hairpin structure.

公开(公告)号：US11286795B2

公开(公告)日：2022-03-29

申请号：US16897874

申请日：2020-06-10

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray

IPC: F01D5/30 ,  F02C7/36 ,  F02C7/32 ,  F01D15/12 ,  F01D15/10 ,  F02C9/00 ,  F02C9/22 ,  F02K1/76 ,  F01D5/12 ,  F01D9/02 ,  F01D5/18 ,  F02C7/264 ,  F01D7/00 ,  F01D9/04 ,  F01D17/16 ,  B64C1/06 ,  B64D27/12 ,  F01D25/12 ,  B32B7/022 ,  B64C1/12 ,  B64D7/00 ,  B64C1/38 ,  B64C1/00

Abstract: A gas turbine engine is provided. The gas turbine engine defines a radial direction. The engine includes: an airfoil positioned within an airflow and extending between a root end and a tip along the radial direction; and a mount coupled to or formed integrally with the root end of the airfoil for mounting the airfoil to the engine, the mount including an outer surface along the radial direction exposed to the airflow and defining an air-cooling channel extending between an inlet and an outlet, the inlet positioned on the outer surface of the mount.

公开(公告)号：US11242150B2

公开(公告)日：2022-02-08

申请号：US16015283

申请日：2018-06-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Viswanadha Gupta Sakala ,  Ravindra Shankar Ganiger ,  Nicholas Joseph Kray

IPC: B64D15/12 ,  H01L51/42 ,  H01L51/00

Abstract: An aircraft can include an anti-icing system. The anti-icing system can include an array of carbon nanotubes thermally coupled to at least a first exposed surface of the aircraft. The anti-icing system can also include an array of solar cells carried by the aircraft and electrically coupled to the array of carbon nanotubes.

公开(公告)号：US11131247B2

公开(公告)日：2021-09-28

申请号：US15883336

申请日：2018-01-30

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain ,  Srinivasarao Surapu

IPC: F02C7/32 ,  F16C3/02 ,  B33Y80/00 ,  F01D5/06 ,  B22F5/10 ,  B33Y10/00 ,  B22F10/20

Abstract: A rotating shaft and a method for additively manufacturing the rotating shaft are provided. The rotating shaft includes an elongated body extending along an axial direction and including an inner surface that defines a hollow central portion. An internal support structure extends from the inner surface into the hollow central portion to stiffen the rotating shaft and provide a high stiffness-to-weight ratio. The internal support structures may include stiffening ribs, truss structures, mesh structures, solid disks, and/or regions having a decreased density relative to the elongated body. The elongated body and some or all internal features may be integrally formed as a single monolithic component.

公开(公告)号：US11052982B2

公开(公告)日：2021-07-06

申请号：US15295168

申请日：2016-10-17

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Stefaan Guido Van Nieuwenhove ,  Peggy Lynn Baehmann

IPC: B63H1/20 ,  B63H1/26

Abstract: A blade member includes a leading edge, a trailing edge, and a blade body extending therebetween. The blade member also includes a dovetail, a transition region, and a transition relief. The dovetail includes a dovetail chord line extending between an axially forward face of the dovetail and an axially aft face of the dovetail. The dovetail chord line has a dovetail chord length. The transition region is formed between the blade body and the dovetail. The blade body and the transition region form a blade body transition chord line at the interface of the blade body and the transition region which has a blade body transition chord length. The transition relief includes a geometric relief in at least one of a forward and an aft end of the transition region and the dovetail. The dovetail chord length is less than the blade body transition chord length.

公开(公告)号：US11047058B2

公开(公告)日：2021-06-29

申请号：US15304682

申请日：2015-04-02

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Qiang Li ,  Nicholas Joseph Kray ,  Michael W. Peretti ,  Tod Winton Davis

IPC: C25D1/02 ,  C25D1/00 ,  F04D29/32 ,  F04D29/38

Abstract: A method for making a metallic leading edge guard of the type having a nose with first and second wings extending therefrom is disclosed. The method includes machining from a metallic blank a first half comprising a first portion of the nose and one of the wings, wherein the first portion of the nose includes an interface surface; and electroforming a second half comprising a second portion of the nose and the second wing, wherein the second half is joined to the first half at the interface surface.

公开(公告)号：US10815816B2

公开(公告)日：2020-10-27

申请号：US16139645

申请日：2018-09-24

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain ,  Manoj Kumar Jain

IPC: F01D11/24 ,  F02C9/18 ,  F02C6/08 ,  F02K3/06

Abstract: A propulsion system including a casing surrounding a fan rotor assembly is provided. The casing includes an outer layer material defining a first coefficient of thermal expansion (CTE) and an inner layer material. The casing further includes a spring member disposed between the outer layer material and the inner layer material coupling the outer layer material and the inner layer material. The spring member is coupled to each of the outer layer material and the inner layer material within a flow passage defined between the outer layer material and the inner layer material. The spring member defines a second CTE greater than the first CTE.

公开(公告)号：US10738630B2

公开(公告)日：2020-08-11

申请号：US15898690

申请日：2018-02-19

Applicant: General Electric Company

Inventor： Qiang Li ,  Nicholas Joseph Kray ,  Gerald Alexander Pauley ,  Ming Xie ,  Jorge Orlando Lamboy ,  Tod Winton Davis

IPC: F01D5/22 ,  F01D9/04 ,  F01D5/28 ,  F01D25/24 ,  F01D5/30 ,  F01D11/00

Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.