公开(公告)号：US11053848B2

公开(公告)日：2021-07-06

申请号：US15878759

申请日：2018-01-24

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 outer wall defining an internal fluid passageway in fluid communication with a fluid supply and terminating in discharge ports that eject a flow of fluid into the compressor section of the gas turbine engine. The internal fluid passageway may also be in fluid communication with heating plenums of a first plurality of airfoils for heating those airfoils.

公开(公告)号：US10927703B2

公开(公告)日：2021-02-23

申请号：US15705712

申请日：2017-09-15

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Benjamin James Roby ,  Vijesh Shetty Anangoor ,  Nitesh Jain ,  Sreekanth Kumar Dorbala ,  Nagamohan Govinahalli Prabhakar ,  K Phani SriKrishna Chinnapragada

IPC: F01B25/16 ,  F01D21/04 ,  F02C7/04 ,  F01D25/24

Abstract: Fan blade containment system includes a composite fan case with an annular composite shell extending from forward flange downstream to aft flange, and circumferentially varying thickness portion of composite shell. Annular composite back sheet spaced radially outwardly of annular composite shell has annular filler layer disposed radially therebetween. Annular forward and aft seams between annular composite shell and composite back sheet may axially trap filler layer. Circumferentially varying thickness portion may include aftwardly extending fingers of composite back sheet in aft seam and first thickness of fingers thicker than second thickness of composite shell circumferentially between fingers. Composite shell may extend from forward flange to aft flange. Aft flange bolted to metallic flange of metallic fan casing aft of aft flange. Containment system may circumscribe and surround fan and fan blades of gas turbine engine fan section.

公开(公告)号：US10760428B2

公开(公告)日：2020-09-01

申请号：US16161296

申请日：2018-10-16

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain

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

Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a leading edge sheath coupled to the leading edge of the airfoil. The leading edge sheath includes a flange extending from a frangible line toward the tip along the span and defining a first width along the chord at each point along the span S. The leading edge sheath further includes a base extending from the frangible line at least partially along the span to the root and defining a second width along the chord at a point along the span of the frangible line such that the second width is greater than the first width.

公开(公告)号：US10724376B2

公开(公告)日：2020-07-28

申请号：US15891401

申请日：2018-02-08

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Nitesh Jain ,  Nagashiresha Gontla ,  Narendra Digamber Joshi ,  Paul Gerard Marsland ,  Wayne Allen Spence

IPC: F01D5/12 ,  F01D5/30

Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.

公开(公告)号：US20200132087A1

公开(公告)日：2020-04-30

申请号：US16170254

申请日：2018-10-25

Applicant: General Electric Company

Inventor： Arun Kumar ,  Nitesh Jain ,  Nicholas Joseph Kray ,  Thomas Ory Moniz ,  Andrew Breeze-Stringfellow

IPC: F04D29/66 ,  F01D5/14 ,  F02K3/06

Abstract: A noise reducing airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a pressure side, a suction side, and a trailing edge sheath including an outer surface coupled to the trailing edge of the airfoil. The trailing edge sheath extends at least partially along the chord on the pressure and suction sides at each point along the span within the trailing edge sheath. The trailing edge sheath defines a fluid passageway extending along at least a portion of the span. Further, the trailing edge sheath defines at least one aperture on at least one of the pressure side, the suction side, or trailing edge fluidly coupling the fluid passageway to the outer surface.

公开(公告)号：US20200116046A1

公开(公告)日：2020-04-16

申请号：US16161270

申请日：2018-10-16

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain

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

Abstract: An airfoil defining a span extending between a root and a tip. The airfoil includes a retaining member extending at least partially between a leading edge and a trailing edge defining a frangible line extending at least partially along a chord at a point along the span of the retaining member. The airfoil further includes a frangible airfoil portion extending between the tip and the frangible line. The frangible airfoil portion includes a first plurality of composite plies, at least one composite ply of the first plurality of composite plies wraps around the retaining member. The airfoil includes a residual airfoil portion extending from the frangible line to the root including a second plurality of composite plies, at least one composite ply of the second plurality of composite plies wraps around the retaining member. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.

公开(公告)号：US10436061B2

公开(公告)日：2019-10-08

申请号：US15486789

申请日：2017-04-13

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: F01D25/24 ,  F01D21/04 ,  F04D29/52

Abstract: A backsheet for use in a turbine engine fan case includes a first portion including a first portion first end and an opposing first portion second end. The first portion is tapered between the first portion first end and the first portion second end. The backsheet also includes a second portion coupled to the first portion. The second portion includes a second portion first end and an opposing second portion second end. The second portion defines a constant thickness between the second portion first end and the second portion second end.

公开(公告)号：US20190284943A1

公开(公告)日：2019-09-19

申请号：US15923545

申请日：2018-03-16

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Paul Gerard Marsland ,  Wayne Allen Spence ,  Abhijeet Yadav ,  Samar Jyoti Kalita ,  Nitesh Jain ,  Narendra D. Joshi

IPC: F01D7/02 ,  F01D5/14

Abstract: An airfoil for a turbomachinery rotor includes: a body having a first density, the body defining a pressure side and a suction side, the pressure side and suction side intersecting at a leading edge and a trailing edge; and a mass positioned within the body and having a second density, wherein the second density is greater than the first density, wherein the mass is offset from a center of gravity of the body in at least one axis.

公开(公告)号：US20190234313A1

公开(公告)日：2019-08-01

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

CPC classification number: F02C7/32 ,  B22F3/1055 ,  B22F5/10 ,  B33Y10/00 ,  B33Y80/00 ,  F16C3/023

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：US10145382B2

公开(公告)日：2018-12-04

申请号：US14985169

申请日：2015-12-30

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Jan Christopher Schilling ,  Nitesh Jain ,  Abhijit Roy

IPC: F01D11/00 ,  F04D29/32 ,  F04D29/02 ,  F01D5/14 ,  F01D5/28 ,  F01D5/30

Abstract: A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.