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1.发明申请公开(公告)号：US20180010469A1
公开(公告)日：2018-01-11
申请号：US15547655
申请日：2015-12-08
CPC分类号： C04B41/81 , C04B41/91 , C23C4/134 , C23C16/045 , F01D5/14 , F01D5/147 , F01D5/18 , F01D5/186 , F01D5/28 , F01D5/282 , F01D5/288 , F01D9/023 , F01D11/08 , F01D11/12 , F01D11/122 , F04D29/324 , F04D29/542 , F04D29/5853 , F05D2220/32 , F05D2230/10 , F05D2230/312 , F05D2230/313 , F05D2230/90 , F05D2240/35 , F05D2250/132 , F05D2250/294 , F05D2250/60 , F05D2300/502 , F05D2300/5023 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y02T50/676 , Y02T50/6765
摘要： Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have furcated engineered groove features (EGFs) (403, 404, 418, 509, 511, 512) that cut into the outer surface of the component's thermal barrier coating (TBC). In some embodiments, the EGF planform pattern defines adjoining outer hexagons (560, 640, 670, 690, 710). In some embodiments, the EGF pattern further defines within each outer hexagon (560, 640, 670, 690, 710) a planform pattern of adjoining inner polygons (570, 580, 590, 600, 610, 680, 682, 700, 702, 704, 705, 720). At least three respective groove segments (509, 511, 512) within the EGF pattern (506, 507, 508) converge at each respective outer hexagonal vertex (510, 564) or inner polygonal vertex (574, 564, 604, 614) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (σA) is furcated (σB, σC) at each successive vertex juncture.
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公开(公告)号：US20160010865A1
公开(公告)日：2016-01-14
申请号：US14765370
申请日：2014-01-17
发明人： Michael Clossen-von Lanken Schulz , Kai Kadau , Jens Kleinfeld , Georg Rollmann , Kai-Uwe Schildmacher , Kagan Özkan
CPC分类号： F23R3/283 , B23P15/00 , F23C2900/07021 , F23D2213/00 , F23D2900/00018 , F23R2900/00005
摘要： A method for producing a fuel lance for a burner, in particular for a gas turbine burner, has at least the following steps: creating a fuel lance body having a tip that has a cooling air duct, which opens into an exit opening extending around a longitudinal axis of the fuel lance body, and a nozzle face, which is arranged around the exit opening and has a plurality of fuel nozzles; determining a spatial distribution of a heat input, to which the nozzle face is subjected during operation when a fuel flowing out through the fuel nozzles is burnt; and applying a thermally insulating layer onto the nozzle face in accordance with the spatial distribution of the heat input. A fuel lance is produced with the method. A burner has such a fuel lance.
摘要翻译： 一种用于燃烧器的燃料喷枪的制造方法，特别是用于燃气轮机燃烧器的方法，至少具有以下步骤：产生燃料喷枪体，其具有具有冷却风道的喷嘴，所述冷却风道开口到围绕 燃料喷枪主体的纵向轴线和喷嘴面，其布置在出口周围并且具有多个燃料喷嘴; 确定在通过燃料喷嘴流出的燃料燃烧时在操作期间喷嘴面经受的热输入的空间分布; 以及根据热输入的空间分布将绝热层施加到喷嘴面上。 用该方法生产燃料喷枪。 燃烧器具有这样的燃料喷枪。
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3.发明申请公开(公告)号：US20180066527A1
公开(公告)日：2018-03-08
申请号：US15547709
申请日：2015-12-08
CPC分类号： F01D5/288 , C23C4/02 , C23C4/073 , C23C4/18 , C23C28/3215 , C23C28/3455 , F01D5/186 , F01D11/122 , F05D2230/30 , F05D2230/31 , F05D2230/90 , F05D2240/11 , F05D2250/11 , F05D2250/12 , F05D2250/132 , F05D2250/294 , F05D2260/22141
摘要： Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have vertically aligned engineered surface features (ESFs) (632, 634) and furcated engineered groove features (EGFs) (642, 652). A planform pattern of EGFs (642, 652) is cut into the outer surface of the component's thermal barrier coating (TBC). The EGF pattern includes a planform pattern of overlying vertices (644) respectively in vertical alignment with an underlying corresponding ESF (632, 634). At least three respective groove segments (642, 652, 642) within the EGF pattern (640) converge at each respective vertex (644) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (σA) is furcated (σB, σC) at each successive vertex juncture.
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公开(公告)号：US20200331069A1
公开(公告)日：2020-10-22
申请号：US16755610
申请日：2017-11-13
摘要： A component for a gas turbine engine can be made via additive manufacturing. During the additive manufacturing process a powder can be used that comprises a superalloy material (12) and carbon nanostructures (14a, 14b). Components made using the powder can have preferred characteristics at certain locations through the use of the carbon nanostructure based additive manufacturing powder.
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公开(公告)号：US20170044995A1
公开(公告)日：2017-02-16
申请号：US15306567
申请日：2015-04-22
发明人： Christian Amann , Björn Beckmann , Eberhard Deuker , Kai Kadau , Boris Ferdinand Kock , Georg Rollmann , Sebastian Schmitz , Marcel Zwingenberg
IPC分类号： F02C9/28
CPC分类号： F02C9/28 , F02C9/00 , F05D2260/821 , F05D2270/08 , F05D2270/301 , F05D2270/303
摘要： A method for selecting operating points of a gas turbine while taking into consideration at least one controlled variable, the operating points being defined at least by parameter combinations of manipulated variables, wherein the operating points are automatically selected on the basis of already known parameter combinations by using an interpolation method, the Kriging interpolation method being used as the interpolation method.
摘要翻译： 一种用于在考虑至少一个受控变量的情况下选择燃气轮机的操作点的方法，所述操作点至少由所述操作变量的参数组合来定义，其中所述操作点根据已知的参数组合被自动选择， 使用插值法，将Kriging插值法用作插值法。
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