公开(公告)号：US10392950B2

公开(公告)日：2019-08-27

申请号：US14706003

申请日：2015-05-07

Applicant: General Electric Company

Inventor： Victor Hugo Silva Correia ,  Brian Kenneth Corsetti ,  Mark Broomer

IPC: F01D9/04 ,  F01D25/24 ,  F01D25/00 ,  F01D25/10

Abstract: A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.

公开(公告)号：US10301953B2

公开(公告)日：2019-05-28

申请号：US15486350

申请日：2017-04-13

Applicant: General Electric Company

Inventor： Victor Hugo Silva Correia

IPC: F01D9/04 ,  F01D11/00 ,  F01D25/24

Abstract: Turbine nozzle segments and systems are provided. For example, a turbine nozzle segment comprises an airfoil extending axially between leading and trailing edges; an inner band defining a portion of a flow path inner boundary; and an outer band defining a portion of a flow path outer boundary. An airfoil trailing edge portion defines the trailing edge and extends axially beyond the inner and outer bands such that the trailing edge is defined axially aft of the inner and outer band aft ends. An exemplary turbine nozzle system comprises the turbine nozzle segment, an outer member positioned aft of the outer band at the trailing edge portion outer end to define the flow path outer boundary along the trailing edge portion, and an inner member positioned aft of the inner band at the trailing edge portion inner end to define the flow path inner boundary along the trailing edge portion.

公开(公告)号：US20180283194A1

公开(公告)日：2018-10-04

申请号：US15474544

申请日：2017-03-30

Applicant: General Electric Company

Inventor： Victor Hugo Silva Correia

IPC: F01D11/04 ,  F02C3/04 ,  F01D9/04

CPC classification number: F01D11/04 ,  F01D9/04 ,  F01D11/005 ,  F02C3/04 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2300/6033

Abstract: A sealing system for sealing a gap between two adjacent components includes a first component including a sealing face, a second component, and a seal cap. The second component includes a seal ridge extending from a surface of the second component towards the sealing face, and a fluid conduit extending through the second component and the seal ridge, the fluid conduit configured to channel a seal activating fluid from a fluid source. The seal cap is configured to matingly engage the seal ridge, and includes an end wall positionable between the sealing face and the seal ridge, and a pair of seal legs extending from the end wall towards the surface of the second component.

公开(公告)号：US20180171808A1

公开(公告)日：2018-06-21

申请号：US15386000

申请日：2016-12-21

Applicant: General Electric Company

Inventor： Victor Hugo Silva Correia ,  Robert Francis Manning ,  George Joe-Kueng Chan ,  James Earl Kopriva

IPC: F01D9/04 ,  F01D9/02 ,  F01D17/02

Abstract: An assembly for a turbine engine comprises a circumferential band defining an air flow path, a component having a leading edge and extending from the band into the flow path, and a trough located in a surface of the band along the leading edge.

公开(公告)号：US20170159451A1

公开(公告)日：2017-06-08

申请号：US15162687

申请日：2016-05-24

Applicant: General Electric Company

Inventor： Jared Peter Buhler ,  Ronald Scott Bunker ,  Victor Hugo Silva Correia ,  Brian Kenneth Corsetti

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/20 ,  F05D2240/307 ,  F05D2260/202 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. A tip shelf can be defined in the pressure or suction sidewalls. A film hole can extend to the tip shelf, such that the film hole can be shaped to direct a flow of cooling fluid to the film hole to improve film cooling at the tip shelf.

公开(公告)号：US20170159450A1

公开(公告)日：2017-06-08

申请号：US14960991

申请日：2015-12-07

Applicant: General Electric Company

Inventor： Jared Peter Buhler ,  Ronald Scott Bunker ,  Victor Hugo Silva Correia ,  Brian Kenneth Corsetti

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/20 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/676

Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.

公开(公告)号：US20170130599A1

公开(公告)日：2017-05-11

申请号：US14936783

申请日：2015-11-10

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Victor Hugo Silva Correia

IPC: F01D11/00 ,  B22F3/105 ,  B23K26/342 ,  C04B35/64 ,  B28B1/00 ,  B29C67/00 ,  F01D9/04 ,  B22F7/02

CPC classification number: F01D11/005 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F7/02 ,  B22F7/08 ,  B22F2999/00 ,  B23K26/342 ,  B28B1/001 ,  B29C64/153 ,  B29L2031/08 ,  B33Y10/00 ,  B33Y80/00 ,  C04B35/64 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2240/128 ,  F05D2240/55 ,  F05D2260/36 ,  F05D2300/17 ,  Y02P10/295 ,  Y02T50/672 ,  B22F2005/005

Abstract: A method of forming a structure in a turbine component having a seal slot, the slot including walls defining an opening therebetween, the method includes the step of using an additive manufacturing process to form a neck structure on a wall so as to reduce a size of the opening.

公开(公告)号：US11918943B2

公开(公告)日：2024-03-05

申请号：US17993082

申请日：2022-11-23

Applicant: General Electric Company

Inventor： Timothy Deryck Stone ,  Gregory Michael Laskowski ,  Robert Proctor ,  Curtis Stover ,  Robert Francis Manning ,  Victor Hugo Silva Correia ,  Jared Peter Buhler ,  Robert Carl Murray ,  Corey Bourassa ,  Byron Andrew Pritchard, Jr. ,  Jonathan Russell Ratzlaff

IPC: B01D45/16 ,  B04C3/00 ,  B04C3/06 ,  F01D5/18 ,  F01D9/06 ,  F02C6/08 ,  F02C7/052 ,  F02C7/18 ,  F02K3/04

CPC classification number: B01D45/16 ,  B04C3/06 ,  F01D5/189 ,  F01D9/065 ,  F02C6/08 ,  F02C7/052 ,  F02C7/18 ,  B04C2003/003 ,  B04C2003/006 ,  F02K3/04 ,  F05D2260/607 ,  Y02T50/60

Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.

公开(公告)号：US11541340B2

公开(公告)日：2023-01-03

申请号：US17325650

申请日：2021-05-20

Applicant: General Electric Company

Inventor： Timothy Deryck Stone ,  Gregory Michael Laskowski ,  Robert Proctor ,  Curtis Stover ,  Robert Francis Manning ,  Victor Hugo Silva Correia ,  Jared Peter Buhler ,  Robert Carl Murray ,  Corey Bourassa ,  Byron Andrew Pritchard, Jr. ,  Jonathan Russell Ratzlaff

IPC: B01D45/16 ,  F02C7/18 ,  B04C3/06 ,  B04C3/00 ,  F02C6/08 ,  F01D5/18 ,  F01D9/06 ,  F02C7/052 ,  F02K3/04

Abstract: A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.

公开(公告)号：US10815806B2

公开(公告)日：2020-10-27

申请号：US15613676

申请日：2017-06-05

Applicant: General Electric Company

Inventor： Victor Hugo Silva Correia ,  Robert Francis Manning

IPC: F01D9/06 ,  F01D5/18

Abstract: An apparatus and method for separating dust from a dirty air flow within an airfoil assembly for a turbine engine. The air foil assembly can include a pair of vanes defining a nozzle through which a flow of air can move. At least one of the vanes can include an insert located within an interior of the vane and having a set of holes.