公开(公告)号：US20220307388A1

公开(公告)日：2022-09-29

申请号：US17210845

申请日：2021-03-24

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain

IPC: F01D25/24 ,  F01D21/04

Abstract: Hybrid composite components, such as gas turbine engine containment assemblies, and methods of forming such components are provided. For example, a hybrid composite component comprises an annular composite shell and an annular metallic shell joined with the composite shell. At least one segment of the metallic shell interlocks with the composite shell or another segment of the metallic shell along an axial length. An exemplary containment assembly comprises a containment case extending along an axial direction about a longitudinal centerline of the gas turbine engine. The containment case has an inner surface and an outer surface spaced apart along a radial direction and includes an annular composite shell joined with an annular metallic shell. The metallic shell defines a first portion of the inner surface and the composite shell defines a second portion of the inner surface.

公开(公告)号：US11454118B2

公开(公告)日：2022-09-27

申请号：US17012595

申请日：2020-09-04

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：US11434781B2

公开(公告)日：2022-09-06

申请号：US16161233

申请日：2018-10-16

Applicant: General Electric Company

Inventor： Nitesh Jain ,  David William Crall ,  Nicholas Joseph Kray ,  Daniel Edward Mollmann

IPC: F01D21/04 ,  F01D5/14 ,  F01D5/28 ,  B33Y80/00

Abstract: An airfoil defining a span extending between a root and a tip. The airfoil includes a frangible airfoil portion extending between a leading edge and a trailing edge and extending between the tip and a fusion line along the span. The frangible airfoil portion includes a first material defining a first modulus of elasticity and further defines an internal cavity. The airfoil includes a residual airfoil portion coupled to the frangible airfoil portion extending from the fusion line to the root along the span and including a second material defining a second modulus of elasticity greater than the first modulus of elasticity. The residual airfoil portion meets the frangible airfoil portion at the fusion line.

公开(公告)号：US11428112B2

公开(公告)日：2022-08-30

申请号：US17063266

申请日：2020-10-05

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. An example casing includes an outer layer material, an inner layer material including first openings extended partially through the inner layer material along a radial direction of a first side of the inner layer material, and second openings extended partially through the inner layer material along the radial direction of a second side of the inner layer material opposite the first side, and a spring member coupled to the outer layer material and the inner layer material.

公开(公告)号：US20220082022A1

公开(公告)日：2022-03-17

申请号：US17024212

申请日：2020-09-17

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Nitesh Jain

IPC: F01D5/08

Abstract: A rotor disk for a gas turbine engine includes a disk body having a central bore extending therethrough. The disk body includes a bore body that extends around the central bore, a web that extends radially outward from the bore body having decreased thickness relative to the bore body and a peripheral rim that is located at an outer end of the web. The peripheral rim includes blade mounting structures for engaging complimentary mounting structures of rotor blades. The bore body has a bore cavity that extends continuously through the bore body and about an entire periphery of the central bore. The bore cavity has a central axis that forms a circle about the central bore.

公开(公告)号：US11242763B2

公开(公告)日：2022-02-08

申请号：US16166602

申请日：2018-10-22

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Andreas Mastorakis ,  Manoj Kumar Jain ,  Nagamohan Govinahalli Prabhakar

IPC: F01D11/00 ,  F01D5/02

Abstract: A platform for use between adjacent propulsion rotor airfoils joined to a rotor disk to provide an inner flowpath boundary includes: an axially extending I-beam supporting a radially outer skin having a flowpath surface; the I-beam including an inner I-flange disposed at an inner edge of an axially extending I-web, and an outer I-flange disposed at an outer edge of the I-web; the I-beam including a laterally-extending forward end flange at a forward end of the I-web, and a laterally-extending aft end flange at an aft end of the I-web; and the radially outer skin disposed on top of and joined to the radially outer I-flange such that the forward end flange and the aft end flange abut the outer skin.

公开(公告)号：US11215069B2

公开(公告)日：2022-01-04

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 ,  F01D25/24

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：US11207821B2

公开(公告)日：2021-12-28

申请号：US15880818

申请日：2018-01-26

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Wendy Wenling Lin ,  Arthur William Sibbach ,  Aaron Todd Sellinger

IPC: B29C55/28 ,  B29C53/08 ,  B29C53/82 ,  B32B1/08 ,  B29L23/00 ,  B29K101/12 ,  B29C53/84

Abstract: A method of making a 3D tube and the 3D tube made thereby. The method comprises: inserting a deflated pre-formed bladder into the 3D tube; and inflating the pre-formed bladder to deform the 3D tube and make the 3D tube have a substantially similar shape as that of the pre-formed bladder inflated.

公开(公告)号：US20210339867A1

公开(公告)日：2021-11-04

申请号：US17071379

申请日：2020-10-15

Applicant: General Electric Company

Inventor： David William Crall ,  Nicholas Joseph Kray ,  Douglas Duane Ward ,  Brandon Wayne Miller

IPC: B64D7/00 ,  B64D27/12 ,  B64C1/12 ,  B32B7/022

Abstract: An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.

公开(公告)号：US20210108518A1

公开(公告)日：2021-04-15

申请号：US16897874

申请日：2020-06-10

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray

IPC: F01D5/18 ,  F01D5/30

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.