公开(公告)号：US10450867B2

公开(公告)日：2019-10-22

申请号：US15042635

申请日：2016-02-12

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/14 ,  F01D9/04 ,  F04D29/68 ,  F04D29/32 ,  F04D29/54 ,  F15D1/00

Abstract: A component stage for a turbomachine includes a component section. The component section includes a flowpath surface at least partially exposed to a core air flowpath defined by the turbomachine, when the component stage is installed in the turbomachine. The component further includes a plurality of sequentially arranged riblets on the flowpath surface, the plurality of sequentially arranged riblets customized for an anticipated location of the flowpath surface within the turbomachine by defining one or both of a non-uniform geometry or a non-uniform spacing.

公开(公告)号：US10378444B2

公开(公告)日：2019-08-13

申请号：US14829678

申请日：2015-08-19

Applicant: General Electric Company

Inventor： Robert Francis Manning ,  Ronald Scott Bunker ,  Robert Frederick Bergholz ,  Robert David Briggs

IPC: F02C3/00 ,  F02C7/18 ,  F01D5/18

Abstract: An engine component for a gas turbine engine includes a film-cooled recess comprising a contoured portion defining a step. A hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow are fluidly coupled by a passage through the engine component. The passage further comprises an inlet in the cooling surface and an outlet in the step. The inlet, passage and outlet are oriented such that the cooling fluid flowing through the passage and exiting the outlet diffuses within the contoured portion prevents premature mixing out with the hot fluid flow.

公开(公告)号：US20180328190A1

公开(公告)日：2018-11-15

申请号：US16039731

申请日：2018-07-19

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D9/06 ,  F04D29/58 ,  F01D9/02 ,  F01D25/12 ,  F04D29/32 ,  F04D29/54 ,  F23R3/06 ,  F23R3/00

CPC classification number: F01D5/186 ,  F01D9/02 ,  F01D9/065 ,  F01D25/12 ,  F04D29/324 ,  F04D29/542 ,  F04D29/545 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2250/312 ,  F05D2250/314 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/676

Abstract: An engine component for a gas turbine engine can generate a hot combustion gas flow and provide a cooling fluid flow. A wall can separate the hot combustion gas flow from the cooling fluid flow. Multiple film holes can be disposed in the wall, having an inlet adjacent the cooling fluid flow and an outlet at the hot combustion gas flow such that the cooling fluid flow can be provided to the hot combustion gas flow. The film holes further comprise inlets, such that the inlets can be arranged with the inlets having at least one of a different orientation relative to one another or are non-aligned with each other relative to the cooling fluid flow.

公开(公告)号：US20170328221A1

公开(公告)日：2017-11-16

申请号：US15152887

申请日：2016-05-12

Applicant: General Electric Company

Inventor： Jason Randolph Allen ,  Ronald Scott Bunker

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12

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 an opening. A framework can be disposed in the opening adapted to reduce the required flow through the opening to increase the efficiency of the engine and improve cooling.

公开(公告)号：US20170328207A1

公开(公告)日：2017-11-16

申请号：US15153122

申请日：2016-05-12

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/28

CPC classification number: F01D5/183 ,  F01D5/147 ,  F01D5/288 ,  F05D2220/30 ,  F05D2260/203 ,  F05D2300/5023 ,  F05D2300/514

Abstract: A turbine component is configured to be cooled by structured porosity cooling. The component includes: a wall; a contiguous porous layer that is part of the wall; a first zone defined in the porous layer such that it has a first structured porosity, and a second zone defined in the layer such that it has a second structured porosity. The first structured porosity is different from the second structured porosity.

公开(公告)号：US20170234140A1

公开(公告)日：2017-08-17

申请号：US15043513

申请日：2016-02-13

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Robert David Briggs ,  Jason Randolph Allen ,  Kevin Robert Feldmann

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D5/188 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2250/185 ,  F05D2260/2212 ,  F05D2260/607 ,  Y02T50/676

Abstract: A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define a cooling circuit within the airfoil. The cooling circuit can have at least one tip turn at the partial-length rib, having at least on fastback turbulator disposed at least partially within the tip turn.

公开(公告)号：US20170159675A1

公开(公告)日：2017-06-08

申请号：US14957978

申请日：2015-12-03

Applicant: General Electric Company

Inventor： Mohamed El Hacin Sennoun ,  Ronald Scott Bunker

IPC: F04D29/58 ,  F02C7/16 ,  F02C7/36 ,  F02K3/06 ,  F01D9/06 ,  F02C3/04 ,  F02K3/115

CPC classification number: F04D29/5826 ,  F01D9/065 ,  F02C3/04 ,  F02C7/143 ,  F02C7/16 ,  F02C7/185 ,  F02C7/36 ,  F02C9/18 ,  F02K3/06 ,  F02K3/115 ,  F04D29/563 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/676

Abstract: An apparatus 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 routing a liquid coolant through the vanes of at least some of the compressor stages and through an intercooler to draw heat into the liquid coolant and routing the heated liquid coolant through a heat exchanger comprising a heat exchanger.

公开(公告)号：US20170159566A1

公开(公告)日：2017-06-08

申请号：US14957946

申请日：2015-12-03

Applicant: General Electric Company

Inventor： Mohammed El Hacin Sennoun ,  Ronald Scott Bunker

IPC: F02C7/18 ,  F02K3/06 ,  F02C3/04

CPC classification number: F02C7/18 ,  F01D5/18 ,  F02C3/04 ,  F02C7/185 ,  F02K3/06 ,  F02K3/115 ,  F05D2260/205 ,  F05D2260/208 ,  F05D2260/213 ,  Y02T50/676

Abstract: An apparatus and method of cooling a gas turbine engine including a core with a compressor section in which the compressor section includes a closed loop cooling circuit having a pump, at least one heat pipe extending from at least one of the stationary vanes, a heat exchanger located within the bypass air flow, and a coolant conduit passing fluidly coupled to the pump and heat exchanger and passing by the heat pipe. The pump pumps coolant through the coolant conduit to draw heat from the heat pipes into the coolant to form heated coolant, the heated coolant then passes through the heat exchanger, where the heat is rejected from the coolant to the bypass air to cool the coolant to form cooled coolant, which is then returned to the heat pipes.

公开(公告)号：US20170130591A1

公开(公告)日：2017-05-11

申请号：US14936578

申请日：2015-11-09

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  B22F7/04 ,  C23C24/08

CPC classification number: F01D5/186 ,  B22F3/1055 ,  B22F3/24 ,  B22F5/04 ,  B22F7/04 ,  B22F7/08 ,  B22F2998/10 ,  B22F2999/00 ,  B23K15/0086 ,  B23K15/0093 ,  B23K26/34 ,  B23K26/384 ,  B23K26/389 ,  B23K2101/001 ,  B23K2103/26 ,  B23P2700/06 ,  B33Y10/00 ,  B33Y40/00 ,  C23C24/087 ,  F01D25/285 ,  F05D2230/10 ,  F05D2230/31 ,  Y02P10/295 ,  Y02T50/676 ,  B22F2003/247 ,  B22F5/10

Abstract: A method of forming a passage in a turbine component that includes using an additive manufacturing process to form a first support structure on a first surface of the turbine component; and forming a passage through the first support structure and the turbine component.

公开(公告)号：US20170129014A1

公开(公告)日：2017-05-11

申请号：US14937325

申请日：2015-11-10

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: B22F5/04 ,  B22F7/04 ,  B22F3/105 ,  F01D5/18

CPC classification number: B22F5/04 ,  B22F3/1055 ,  B22F7/08 ,  B22F2005/103 ,  B33Y40/00 ,  B33Y80/00 ,  F01D5/186 ,  F05D2230/10 ,  F05D2230/31 ,  F05D2260/202 ,  Y02P10/295 ,  Y02T50/676

Abstract: A method of forming a cooling hole structure on a turbine component. The turbine component has a component wall with inner and outer surfaces. A bore passes through the component wall and fluidly connects the inner surface and the outer surface. The method includes the steps of: A) forming a recess communicating with the bore and the outer surface; and B) using an additive manufacturing process to form an exit region in the recess.