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公开(公告)号：US20180051571A1
公开(公告)日：2018-02-22
申请号：US15238174
申请日：2016-08-16
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: F01D5/187 , F01D5/28 , F01D9/041 , F01D9/065 , F01D25/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2230/30 , F05D2240/126 , F05D2240/301 , F05D2250/185 , F05D2260/22141 , F05D2300/514 , F05D2300/612 , Y02T50/671 , Y02T50/676
Abstract: An apparatus and method for cooling an engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior having full-length ribs and partial-length ribs to define the cooling circuit, with the partial length ribs defining a turn.
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公开(公告)号：US20180051567A1
公开(公告)日：2018-02-22
申请号：US15238058
申请日：2016-08-16
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: An engine component, such as an airfoil, for a turbine engine having a hole, which can be a film hole, within the outer wall of the engine component where cooling air moves from an interior cavity through the hole to an outer surface of the engine component providing a cooling film on the outer surface of the engine component.
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公开(公告)号：US20170370222A1
公开(公告)日：2017-12-28
申请号：US15191934
申请日：2016-06-24
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: F01D5/005 , B23P6/007 , B23P6/045 , B33Y10/00 , B33Y80/00 , F01D5/18 , F01D5/186 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2230/30 , F05D2230/80 , F05D2240/80 , F05D2260/202 , F05D2300/175
Abstract: Methods for repairing a trailing edge of an airfoil are provided. The method can include removing a portion of the trailing edge of the airfoil to form an intermediate component, and then applying using additive manufacturing a replacement portion on the intermediate component to form a repaired airfoil. The replacement portion defines at least one trailing edge ejection slot.
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公开(公告)号：US20170328210A1
公开(公告)日：2017-11-16
申请号：US15150659
申请日：2016-05-10
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
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.
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公开(公告)号：US20170321564A1
公开(公告)日：2017-11-09
申请号：US15144857
申请日：2016-05-03
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert Charles Groves, II
CPC classification number: F01D9/065 , F01D5/18 , F01D5/187 , F01D9/041 , F01D9/048 , F01D25/12 , F01D25/14 , F01D25/24 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/307 , F05D2260/205 , F05D2260/213 , F05D2300/6033 , Y02T50/676
Abstract: A method for cooling a component of a gas turbine engine includes flowing a cooling airflow through a cooling passage of a turbine rotor blade, wherein the cooling passage includes an inlet and an outlet formed on a blade tip of the turbine rotor blade. The method further includes receiving at least a portion of the cooling airflow exiting the outlet of the cooling passage with an aperture defined in a casing of the gas turbine engine, wherein the casing is spaced from the blade tip along the radial direction. In addition, the method includes providing the cooling airflow received with the aperture defined in the casing to the component of the gas turbine engine through a coolant duct assembly of the gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US20170234150A1
公开(公告)日：2017-08-17
申请号：US15042674
申请日：2016-02-12
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: F01D9/065 , F01D5/18 , F01D25/24 , F05D2220/32 , F05D2230/30 , F05D2260/201 , F05D2260/941 , Y02T50/673 , Y02T50/676
Abstract: A component for a gas turbine engine includes a hot side wall, a plurality of connection walls, and a cold side wall. The hot side wall is exposed to a core air flowpath defined by the gas turbine engine. The cold side wall is spaced from the hot side wall and rigidly connected to the hot side wall through the plurality of connection walls. The hot side wall, connection walls, and cold side wall together define a cooling air cavity. The cold side wall defines a thermal stress relief slot for at least partially accommodating a relative thermal expansion between the hot side wall and the cold side wall to reduce an amount of thermal stress within the component during operation of the component.
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公开(公告)号：US20170234146A1
公开(公告)日：2017-08-17
申请号：US15044697
申请日：2016-02-16
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert David Briggs , Timothy Deryck Stone
CPC classification number: F01D5/188 , F01D5/147 , F01D5/186 , F05D2220/32 , F05D2240/24 , F05D2240/303 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: An airfoil for a turbine engine having a perimeter wall bounding an interior and defining a pressure side and a suction side, a radially extending rib located within the interior and spaced from the leading edge to define a radially extending leading edge chamber, and at least one impingement opening in the rib defining a flow path aligned with the leading edge.
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公开(公告)号：US20170234141A1
公开(公告)日：2017-08-17
申请号：US15044775
申请日：2016-02-16
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert David Briggs
CPC classification number: F01D5/187 , F05D2240/303 , F05D2250/12 , F05D2250/14 , F05D2260/201 , F05D2260/202 , Y02T50/676
Abstract: An airfoil for a turbine engine having first and second radially extending cooling chambers separated by a radially extending rib in which rows of crossover holes pass through the rib and fluidly coupling the first and second chambers.
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公开(公告)号：US09732617B2
公开(公告)日：2017-08-15
申请号：US14089920
申请日：2013-11-26
Applicant: General Electric Company
Inventor： Guanghua Wang , Ronald Scott Bunker , Jeremy Clyde Bailey , James Peter DeLancey , David Benjamin Helmer
CPC classification number: F01D5/186 , F01D5/187 , F01D9/041 , F01D9/065 , F05D2240/304 , F05D2250/13 , F05D2250/131 , F05D2250/14 , F05D2250/141 , F05D2250/324 , F05D2260/2212 , Y02T50/673 , Y02T50/676
Abstract: An airfoil and method of cooling a airfoil including a leading edge, a trailing edge, a suction side, a pressure side and at least one internal cooling channel configured to convey a cooling fluid, is provided. A plurality of trailing edge bleed slots are in fluid communication with the at least one internal cooling channel, wherein a downstream edge of the pressure side of the airfoil lies upstream of a downstream edge of the suction side to expose the plurality of trailing edge bleed slots proximate to the trailing edge of the airfoil. The at least one internal cooling channel is configured to supply the cooling fluid from a source of cooling fluid towards the plurality of trailing edge bleed slots. A plurality of obstruction features are disposed within the at least one internal cooling channel and at a downstream edge of the remaining pressure side. The one or more obstruction features are configured having a predefined substantially polygon shape, to distribute a flow of the cooling fluid and provide distributed cooling to the plurality of trailing edge bleed slots.
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公开(公告)号：US20170226882A1
公开(公告)日：2017-08-10
申请号：US15016645
申请日：2016-02-05
Applicant: General Electric Company
Inventor： Jonathan Russell Ratzlaff , Ronald Scott Bunker
CPC classification number: F01D11/02 , F01D5/081 , F01D5/082 , F01D11/001 , F01D11/04 , F05D2220/32 , F05D2240/10 , F05D2240/24 , F05D2250/184 , F05D2260/20 , Y02T50/676
Abstract: An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one of the axial faces defines a buffer cavity into which a wing extends from the other of the axial faces and having a surface confronting the fluid outlet. A flow reverser is further provided within at least one of the surface or the terminal portion of the other of the axial faces.
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