公开(公告)号：US20170368647A1

公开(公告)日：2017-12-28

申请号：US15191951

申请日：2016-06-24

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: B23P6/00 ,  B23P6/04 ,  F01D5/00 ,  F01D5/28 ,  B33Y10/00 ,  B33Y80/00 ,  F01D9/02 ,  F04D29/32 ,  F04D29/38 ,  F04D29/54 ,  F23R3/00

CPC classification number: B23P6/007 ,  B22F5/04 ,  B22F2007/068 ,  B22F2998/10 ,  B22F2999/00 ,  B23K26/144 ,  B23K26/34 ,  B23K2101/001 ,  B23K2103/05 ,  B23K2103/26 ,  B23P6/005 ,  B23P6/045 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/005 ,  F01D5/186 ,  F01D5/28 ,  F01D9/02 ,  F01D9/065 ,  F04D29/324 ,  F04D29/38 ,  F04D29/542 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2240/35 ,  F05D2260/202 ,  F23R3/002 ,  Y02P10/295 ,  B22F3/1055 ,  B22F2003/247 ,  B22F2003/153 ,  B22F3/24

Abstract: Methods for repairing an airfoil having a damaged region are provided. The method can include removing the damaged portion from the airfoil to form an intermediate component. The damaged portion generally includes an original film hole having an original cross-sectional geometry. Using additive manufacturing, a replacement portion is then applied on the intermediate component to form a repaired component with the replacement portion including a rebuilt film hole having a rebuilt cross-sectional geometry that is different than the original cross-sectional geometry.

公开(公告)号：US20170328215A1

公开(公告)日：2017-11-16

申请号：US15150634

申请日：2016-05-10

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D5/14

Abstract: An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.

公开(公告)号：US20170328213A1

公开(公告)日：2017-11-16

申请号：US15152862

申请日：2016-05-12

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D25/12 ,  F04D29/32 ,  F04D29/54 ,  F23R3/06 ,  F01D5/14 ,  F04D29/58 ,  F01D9/04 ,  F23R3/00

CPC classification number: F01D5/186 ,  F01D5/147 ,  F01D5/18 ,  F01D5/183 ,  F01D5/28 ,  F01D9/041 ,  F01D25/12 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2250/70 ,  F05D2260/202 ,  F05D2260/221 ,  F23R3/002 ,  F23R3/06 ,  Y02T50/672 ,  Y02T50/676

Abstract: An apparatus and method for flowing cooling air through an outer wall of an engine component such as an airfoil. The airfoil having the outer wall can include a skin layer and a porous layer. The skin layer can include a skin cooling circuit for providing the cooling air from an interior of the airfoil to the exterior of the airfoil through the porous layer.

公开(公告)号：US20170328209A1

公开(公告)日：2017-11-16

申请号：US15150647

申请日：2016-05-10

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D5/28

Abstract: An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.

公开(公告)号：US09803939B2

公开(公告)日：2017-10-31

申请号：US14088128

申请日：2013-11-22

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F28F19/06 ,  F28F19/02 ,  C23C24/04 ,  F28F13/18 ,  C23C4/01 ,  C23C4/073

CPC classification number: F28F19/06 ,  C23C4/01 ,  C23C4/073 ,  C23C24/04 ,  F01D5/187 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2260/204 ,  F28F13/185 ,  F28F19/02 ,  Y02T50/672 ,  Y02T50/676

Abstract: A method to modify the shape of a channel in a metallic substrate is described. The method includes the step of applying at least one metallic coating on selected portions of an interior surface of the channel, so as to alter the heat transfer characteristics of the channel during passage of a coolant fluid therethrough. Related articles that contain the modified channels are also described, such as gas turbine engine components.

公开(公告)号：US20170268345A1

公开(公告)日：2017-09-21

申请号：US15071443

申请日：2016-03-16

Applicant: General Electric Company

Inventor： Robert Charles Groves, II ,  Kirk Douglas Gallier ,  Ronald Scott Bunker

IPC: F01D5/18 ,  F01D9/04

Abstract: An airfoil having a radial direction extending away from an engine axis is provided. The airfoil includes an airfoil wall having an airfoil outer surface and an airfoil inner surface, with the airfoil extending radially from a first end to a second end. The airfoil defines a cooling channel interior to the inner surface with a thickness being defined between the airfoil outer surface and the airfoil inner surface. The thickness varies in the radial direction from the first end to the second end along at least one radial cross-section of the airfoil. A turbine nozzle of a turbine engine is also provided, which may include an outer band, an inner band, and the airfoil.

公开(公告)号：US20170234537A1

公开(公告)日：2017-08-17

申请号：US15042586

申请日：2016-02-12

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F23R3/00 ,  F02C3/04

CPC classification number: F23R3/002 ,  F01D5/18 ,  F01D5/186 ,  F01D25/12 ,  F02C3/04 ,  F05D2230/30 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/00018 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: A component for at least one of a combustion section or a turbine section of a gas turbine engine is provided. The combustion section and turbine section of the gas turbine engine at least partially define a core air flowpath, and the component includes a wall. The wall, in turn, includes a hot side and an opposite cold side. The hot side is exposed to and at least partially defines the core air flowpath when the component is installed in the gas turbine engine. The wall is manufactured to include surface contouring on the cold side of the wall to structurally accommodate a thermal management feature of the wall.

公开(公告)号：US20170159568A1

公开(公告)日：2017-06-08

申请号：US14957910

申请日：2015-12-03

Applicant: General Electric Company

Inventor： Mohamed El Hacin Sennoun ,  Ronald Scott Bunker

IPC: F02C7/18 ,  F01D25/24 ,  F04D29/58 ,  F01D5/12 ,  F04D19/02 ,  F01D25/12 ,  F01D9/02

CPC classification number: F02C7/185 ,  F01D5/12 ,  F01D9/02 ,  F01D25/12 ,  F01D25/24 ,  F02C7/143 ,  F02C9/18 ,  F04D19/02 ,  F04D29/5826 ,  F04D29/584 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/14 ,  F05D2240/30 ,  F05D2260/20 ,  F05D2260/211 ,  Y02T50/676

Abstract: A system and method of cooling a gas turbine engine having a compressor with multiple, axially arranged stages of paired rotating blades and stationary vanes located between an outer compressor casing and inner compressor casing, comprising a closed loop cooling of the compressor by extracting compressor air from a first location in the compressor, cooling the extracted air, and introducing the cooled, extracted air at a second location in the compressor, with the second location being upstream of the first location.

公开(公告)号：US20170159449A1

公开(公告)日：2017-06-08

申请号：US14960924

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 ,  F01D5/188 ,  F05D2260/202 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.

公开(公告)号：US20170152749A1

公开(公告)日：2017-06-01

申请号：US14955261

申请日：2015-12-01

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Kevin Robert Feldmann ,  Robert Charles Groves, II

IPC: F01D5/18 ,  F23R3/00 ,  F23R3/06 ,  F01D9/06

CPC classification number: F01D5/186 ,  C23C28/321 ,  C23C28/345 ,  F01D5/288 ,  F01D9/065 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2260/202 ,  F05D2300/15 ,  F05D2300/211 ,  F05D2300/5024 ,  F05D2300/6033 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/676 ,  Y02T50/6765

Abstract: Engine components are provided for a gas turbine engines that generate a hot combustion gas flow. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate generally defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component can also include a coating on at least a portion of the hot surface and on at least a portion of an inner surface defined within the passage.