公开(公告)号：US10328639B2

公开(公告)日：2019-06-25

申请号：US15017104

申请日：2016-02-05

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Stefaan Guido Van Nieuwenhove

IPC: B29C35/02 ,  B29C35/08 ,  B29C65/02 ,  B29C65/14 ,  B29C65/18 ,  B29C70/38 ,  B29C65/00

Abstract: An automated fiber placement (AFP) system includes a tool head with a compaction roller and a first variable heat source. The compaction roller is configured to receive at least one of a fiber and a plurality of fibers formed as a laydown tape, and is controlled to apply the laydown tape to a workpiece at a predetermined speed and direction. The first variable heat source is configured to apply a first amount of heat to the laydown tape. The first amount of heat applied is related to the predetermined speed. The AFP system further includes a second variable heat source configured to apply a second amount of heat to the workpiece. The second amount of heat applied is related to at least one of: a position on the workpiece, a thickness of the workpiece at that position, and a separation distance between the second variable heat source and the workpiece.

公开(公告)号：US20190170012A1

公开(公告)日：2019-06-06

申请号：US15832814

申请日：2017-12-06

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Nitesh Jain ,  Saurabh Sanjay Rasal

IPC: F01D21/08 ,  F02K3/06 ,  F02C7/36 ,  F01D25/16 ,  F16D3/18 ,  F16D1/10

Abstract: A rotor assembly includes a fan rotor shaft coupled to a fan rotor, a low pressure turbine rotor shaft coupled to a low pressure turbine rotor, and a joint device configured to connect the fan rotor shaft to the low pressure turbine rotor shaft, to allow torsion, shear and bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and allow torsion and shear but prevent bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event.

公开(公告)号：US20180283180A1

公开(公告)日：2018-10-04

申请号：US15471729

申请日：2017-03-28

Applicant: General Electric Company

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

IPC: F01D5/14 ,  F15D1/00

Abstract: A turbine engine can comprise a fan section, compressor section, a combustion section, and a turbine section in axial flow arrangement. At least one of the fan section and compressor section can include an airfoil with a leading edge, and a plurality of riblets can be arranged on the leading edge.

公开(公告)号：US20180105246A1

公开(公告)日：2018-04-19

申请号：US15295679

申请日：2016-10-17

Applicant: General Electric Company

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

IPC: B63H1/20

Abstract: An apparatus and system for a propeller assembly are provided. In one aspect, marine propeller assembly includes a plurality of circumferentially-spaced blades that each include a dovetail having a radially inner surface. The marine propeller assembly also includes a hub including a plurality of circumferentially-spaced dovetail receiving portions configured to receive a corresponding dovetail of the plurality of blades. At least one gap is formed between the radially inner surface and at least a portion of the dovetail receiving portion.

公开(公告)号：US09885244B2

公开(公告)日：2018-02-06

申请号：US14418534

申请日：2013-06-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Dong-Jin Shim ,  Tod Winton Davis

IPC: F01D5/28 ,  F01D5/26 ,  F01D5/14 ,  F04D29/32 ,  F04D29/02 ,  C22C19/05 ,  C22C38/02 ,  C22C38/04 ,  C22C38/42 ,  C22C38/48 ,  C22C38/54

CPC classification number: F01D5/26 ,  C22C19/057 ,  C22C38/02 ,  C22C38/04 ,  C22C38/42 ,  C22C38/48 ,  C22C38/54 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2300/171 ,  F05D2300/175 ,  Y02T50/672 ,  Y10T29/49337

Abstract: A metallic leading edge protective strip adapted to provide impact protection for a leading edge of an airfoil of a turbomachine. The protective strip is formed of a stainless steel or a nickel-based alloy and is denser and provides increased strength and elasticity characteristics as compared to an identical protective strip formed of a titanium-based alloy. The protective strip is particularly suitable for use with composite blades and allows for thinner airfoils, thereby improving engine efficiency.

公开(公告)号：US20170373612A1

公开(公告)日：2017-12-28

申请号：US15189026

申请日：2016-06-22

Applicant: General Electric Company

Inventor： Aaron Todd Sellinger ,  Nicholas Joseph Kray

IPC: H02N2/18 ,  G01L1/16 ,  G01K7/02 ,  H01L35/32 ,  F04D29/38

CPC classification number: H02N2/186 ,  C04B35/117 ,  C04B35/52 ,  C04B35/565 ,  C04B35/80 ,  C04B2235/3217 ,  C04B2235/3225 ,  C04B2235/3244 ,  C04B2235/3418 ,  C04B2235/349 ,  C04B2235/5224 ,  C04B2235/5228 ,  C04B2235/5244 ,  F01D5/10 ,  F01D5/16 ,  F01D5/26 ,  F01D5/282 ,  F01D15/10 ,  F01D25/005 ,  F01D25/04 ,  F01D25/06 ,  F03G7/08 ,  F04D29/388 ,  F05D2260/407 ,  F05D2300/6033 ,  G01K7/02 ,  G01L1/16 ,  H01L35/32 ,  H01L41/113 ,  H02N2/181 ,  Y02T50/672 ,  Y02T50/673

Abstract: The present disclosure is directed to an engine component for a gas turbine engine, the engine component including a substrate that includes a composite fiber and defines a surface. An energy harvesting fiber is positioned within the substrate.

公开(公告)号：US20170321714A1

公开(公告)日：2017-11-09

申请号：US15148631

申请日：2016-05-06

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Vikulp Sharma ,  Nicholas Joseph Kray

IPC: F04D29/38 ,  F04D29/02 ,  F04D29/32 ,  F04D29/52

Abstract: A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil body. The metal leading edge further includes a second edge extending axially aftward from the nose along a suction side of the fan blade airfoil body. The first edge and the second edge forming a notch at the conjunction of the first edge, the second edge, and the nose. The metal leading edge also includes a nose length extending from a nose tip to the notch. The nose length at a first radial location is different from the nose length at a second radial location.

公开(公告)号：US09797257B2

公开(公告)日：2017-10-24

申请号：US13709651

申请日：2012-12-10

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Scott Roger Finn ,  Peggy Lynn Baehmann ,  Joel Primmer White

IPC: F01D5/14 ,  F01D5/28 ,  B29D99/00 ,  B29C70/20 ,  B29C70/38 ,  B29L31/08

CPC classification number: F01D5/147 ,  B29C70/202 ,  B29C70/38 ,  B29D99/0025 ,  B29L2031/082 ,  F01D5/282 ,  Y02T50/672

Abstract: A composite article including composite component mounted on a spar including a shank extending heightwise from below component base up into composite component. Tab at an upper end of shank substantially or fully embedded in the composite component and at least one ply surface pattern of the composite component contacting and generally conforming to at least one spar surface pattern on the tab.Spar surface pattern may include spaced apart spar surface protrusions with spar surface spaces therebetween and spar surface protrusions extending outwardly from spar and disposed between tows in ply surface pattern. Tows may be layed up in spar surface spaces. Spar surface pattern may include continuous or segmented spaced spar surface protrusions and spar surface spaces therebetween with tows in ply surface pattern disposed in spar surface spaces. The composite article may be a composite blade or vane including a composite airfoil.

公开(公告)号：US20170268374A1

公开(公告)日：2017-09-21

申请号：US15071264

申请日：2016-03-16

Applicant: General Electric Company

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

IPC: F01D17/14 ,  F02C7/042 ,  F02C9/18 ,  F01D5/14

CPC classification number: F01D17/141 ,  F01D5/148 ,  F01D17/10 ,  F02C7/042 ,  F02C9/18 ,  F04D27/0215 ,  F04D27/023 ,  F04D29/563 ,  F05D2220/32 ,  F05D2250/90 ,  F05D2270/20 ,  F05D2270/60 ,  F05D2270/64 ,  F05D2270/65 ,  F05D2300/501 ,  Y02T50/672 ,  Y02T50/673

Abstract: A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.

公开(公告)号：US20170226865A1

公开(公告)日：2017-08-10

申请号：US15040582

申请日：2016-02-10

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Trevor Howard Wood ,  Dong-Jin Shim ,  Pranav Dhoj Shah

IPC: F01D5/14 ,  F01D5/28 ,  F01D9/04

CPC classification number: F01D5/141 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F01D9/041 ,  F05D2220/323 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/184 ,  F05D2250/29 ,  F05D2300/10 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil assembly including a composite body having a mounting edge and a trailing edge which is secured to a leading edge element defining a 3-D leading edge geometry with both chord and camber variation.