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31.发明申请公开(公告)号：US20150143792A1
公开(公告)日：2015-05-28
申请号：US14089888
申请日：2013-11-26
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: F01D5/187 , F05D2230/31 , F05D2230/90 , Y02T50/672 , Y02T50/676
Abstract: A manufacturing method includes providing a substrate having one or more grooves formed therein. One or more coatings having one or more grooves formed therein are disposed on the substrate and in fluid communication with the one or more grooves in the substrate. A cover coating is disposed on a portion of an outermost surface of the one or more coatings, having one or more cooling outlets formed therein and in fluid communication with the one or more grooves in the one or more coatings. The substrate, the one or more coatings and the cover coating define therein a cooling network for cooling a component. A component having a cooling network defined therein a substrate, one or more coatings disposed on at least a portion of the substrate, and a cover coating disposed over at least a portion of an outermost coating of the one or more coatings.
Abstract translation: 一种制造方法包括提供其中形成有一个或多个凹槽的基板。 其中形成有一个或多个凹槽的一个或多个涂层设置在基底上并且与衬底中的一个或多个凹槽流体连通。 覆盖涂层设置在一个或多个涂层的最外表面的一部分上，其中形成有一个或多个冷却出口并与一个或多个涂层中的一个或多个凹槽流体连通。 衬底，一个或多个涂层和覆盖层在其中限定了用于冷却部件的冷却网。 具有限定在其中的冷却网络的部件，设置在所述基板的至少一部分上的一个或多个涂层以及设置在所述一个或多个涂层的最外涂层的至少一部分上的覆盖涂层。
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32.发明申请公开(公告)号：US20140302278A1
公开(公告)日：2014-10-09
申请号：US13859437
申请日：2013-04-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ronald Scott Bunker
CPC classification number: F01D25/12 , B05D3/002 , B05D3/06 , B05D3/12 , B05D3/14 , C23C4/073 , C23C4/18 , C23C24/04 , F01D5/186 , F01D5/188 , F05D2230/10 , F05D2260/204 , Y02T50/672 , Y02T50/676 , Y02T50/6765 , Y10T428/24322
Abstract: A manufacturing method includes providing a substrate and forming one or more grooves into an outer surface of the substrate or into a coating layer disposed on the outer surface of the substrate and forming one or more grooves into an inner surface of the substrate or into a coating layer disposed on the inner surface of the substrate, to define one or more cooling grooves on the inner surface of the substrate. The method further includes applying a structural coating over at least one of a portion of the outer surface of the substrate or a portion of the coating disposed on the outer surface of the substrate to define one or more cooling channels on the outer surface of the substrate. A component is disclosed fabricated according to the method.
Abstract translation: 一种制造方法包括提供基板并在基板的外表面中形成一个或多个凹槽，或者形成设置在基板的外表面上的涂层，并将一个或多个凹槽形成到基板的内表面或涂层 层，其设置在基板的内表面上，以在基板的内表面上限定一个或多个冷却槽。 所述方法还包括将结构涂层施加在衬底的外表面的一部分中的至少一个上或涂覆在衬底的外表面上的涂层的一部分，以限定衬底的外表面上的一个或多个冷却通道 。 公开了根据该方法制造的部件。
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公开(公告)号：US20140220253A1
公开(公告)日：2014-08-07
申请号：US13627158
申请日：2012-09-26
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: C23C4/005 , B05D3/00 , B05D3/042 , B05D7/22 , C23C4/01 , C23C4/073 , C23C4/11 , C23C4/129 , F01D5/18 , F01D5/187 , F01D5/28 , F01D5/288 , F05D2230/31 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: Methods of pressure coating a target surface of an article comprising one or more grooves formed in an outer surface of an article include fluidly connecting a pressure masker comprising a pressurized masking fluid to one or more coolant supply holes on a first side of the article. The one or more coolant supply holes in fluidic communication with the one or more grooves. Passing the pressurized masking fluid through the one or more grooves from the first side to a second side comprising the target surface at a pressure less than the coating pressure of the coating material, and, coating the target surface with the coating material to allow the coating material to bridge over the one or more grooves and form one or more micro-channels. The pressurized masking fluid passing through the one or more grooves prevents the coating material from permanently altering a cross sectional area of the one or more grooves along its length.
Abstract translation: 包括形成在制品的外表面中的一个或多个凹槽的制品的目标表面的压力涂覆方法包括将包括加压掩模流体的压力掩模流体连接到制品第一侧上的一个或多个冷却剂供应孔。 所述一个或多个冷却剂供应孔与所述一个或多个凹槽流体连通。 将加压掩模流体通过一个或多个凹槽从包含目标表面的第一侧到第二侧，压力小于涂覆材料的涂覆压力，并用涂覆材料涂覆目标表面以允许涂层 材料跨越所述一个或多个凹槽并形成一个或多个微通道。 通过一个或多个凹槽的加压掩模流体防止涂层材料沿其长度永久地改变一个或多个凹槽的横截面面积。
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公开(公告)号：US10822957B2
公开(公告)日：2020-11-03
申请号：US16247711
申请日：2019-01-15
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
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.
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公开(公告)号：US10767489B2
公开(公告)日：2020-09-08
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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Patent Agency Ranking
公开(公告)号：US10605170B2
公开(公告)日：2020-03-31
申请号：US14950677
申请日：2015-11-24
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: An engine component for a gas turbine engine which generates a hot combustion gas flow adjacent a hot surface and provides a cooling fluid flow adjacent a cooling surface comprises a wall separating the hot combustion gas flow and the cooling fluid flow. At least one concavity is provided in the cooling surface and at least one film hole is provided in the cooling surface providing the cooling fluid flow to the hot surface. An inlet for the film hole is spaced from the at least one concavity, located upstream of the at least one concavity and in alignment with the at least one concavity relative to the cooling fluid flow.
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公开(公告)号：US10563514B2
公开(公告)日：2020-02-18
申请号：US15314618
申请日：2015-05-29
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert David Briggs , Shawn Michael Pearson
Abstract: A structure for disrupting the flow of a fluid is provided, the structure comprising: a first lateral wall and a second lateral wall spaced apart from one another a distance across an X-axis; and a turbulator extending between the first lateral wall and the second lateral wall, the turbulator extending away from the floor. The turbulator includes a first front surface extending between the first lateral wall and the second lateral wall, a second front surface extending between the first lateral wall and the second lateral wall, a first rear surface extending between the first lateral wall and the second lateral wall, the first rear surface extending between the first front surface and the floor, and a second rear surface adjoining the first rear surface and extending between the first lateral wall and the second lateral wall, the second rear surface extending between the second front surface and the floor.
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公开(公告)号：US10519779B2
公开(公告)日：2019-12-31
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
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.
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公开(公告)号：US20190316473A1
公开(公告)日：2019-10-17
申请号：US16423313
申请日：2019-05-28
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Zachary Daniel Webster
Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.
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公开(公告)号：US10436068B2
公开(公告)日：2019-10-08
申请号：US15042568
申请日：2016-02-12
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: A gas turbine engine includes a compressor section, combustion section, and turbine section. The turbine section includes a turbine component stage, the turbine component stage including a plurality of turbine components together including a flowpath surface along a circumferential direction of the gas turbine engine. The flowpath surface defines in part a core air flowpath of the gas turbine engine and further defines a contour along the circumferential direction. The contour repeats less frequently than once per turbine component to accommodate a hot gas streak through the turbine section.
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