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公开(公告)号：US07614847B2
公开(公告)日：2009-11-10
申请号：US10996878
申请日：2004-11-24
申请人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter Mcgovern
发明人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter Mcgovern
IPC分类号： F01D11/12
CPC分类号： F01D11/12 , F01D11/122
摘要： A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first plurality of ridges disposed at the base surface such that a first portion of the first plurality of ridges corresponding to a back portion of the turbine bucket is oriented at a first angle with respect to an axis of rotation of the turbine bucket. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.
摘要翻译： 用于改善涡轮机的空气动力学性能的模式包括在涡轮机护罩的基面处以图案设置的材料，使得该材料能够与涡轮机桶的尖端部分磨损接触。 该图案包括设置在基部表面处的第一多个脊，使得对应于涡轮机桶的后部的第一多个脊的第一部分相对于涡轮叶片的旋转轴线以第一角度定向 。 第一多个脊中的每个脊具有第一侧壁和具有第一端和第二端的第二侧壁。 第一和第二侧壁的第一端从基面延伸。 第一和第二侧壁彼此相对倾斜，具有基本上相等但相反的斜面，直到在相应的第一和第二侧壁的第二端处共同限定脊的中心线和顶部。
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公开(公告)号：US20080056889A1
公开(公告)日：2008-03-06
申请号：US11507562
申请日：2006-08-22
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F01D11/02
摘要： An abradable seal is provided to improve turbine performance by physically reducing the clearance between a flange portion of the nozzle and an opposed angel wing/seal plate member of the bucket. The provision of an abradable seal also mitigates angel wing/seal plate tooth or fin wear by providing for abradable contact without metal to metal hard rub.
摘要翻译： 提供可磨损密封件以通过物理地减小喷嘴的凸缘部分和铲斗的相对的天使翼/密封板构件之间的间隙来改善涡轮机性能。 提供可磨损的密封件还通过提供无磨损的接触而减轻天使翼/密封板的齿或翅片磨损，而不会金属与金属的硬摩擦。
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公开(公告)号：US20110044821A1
公开(公告)日：2011-02-24
申请号：US11654182
申请日：2007-01-17
申请人： Raymond Grant Rowe , Tara Easter McGovern , Jane Ann Murphy , Andrew Jay Skoog , William R. Stowell , Paul Thomas Marks , Lisa DeBellis , James H. Clare
发明人： Raymond Grant Rowe , Tara Easter McGovern , Jane Ann Murphy , Andrew Jay Skoog , William R. Stowell , Paul Thomas Marks , Lisa DeBellis , James H. Clare
CPC分类号： C23C4/02 , F01D5/288 , F05D2230/90 , Y02T50/673
摘要： A method of fabricating a component for a gas turbine engine is provided. The method includes applying a bond coat to at least a portion of the component, applying a dense vertically cracked (DVC) thermal barrier coating to at least a portion of the bond coat using a spray mechanism positioned a first distance from the component, and overlying at least a portion of the DVC thermal barrier coating with a soft coat thermal barrier coating using a spray mechanism that is positioned a second distance away from the component, wherein the second distance is greater than the first distance to facilitate adherence of the soft coating thermal barrier coating to the DVC thermal barrier coating.
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公开(公告)号：US08210821B2
公开(公告)日：2012-07-03
申请号：US12168932
申请日：2008-07-08
IPC分类号： F03B3/12
CPC分类号： F01D5/3007 , F01D5/081 , F01D5/087 , F01D11/005 , F01D11/006 , F01D11/02
摘要： A labyrinth seal that may include a first leg positioned about a high-pressure side of the dovetail tab, a second leg positioned about a low-pressure side of the dovetail tab, and a labyrinth chamber positioned between the first leg and the second leg. High-pressure fluid passing through the gap about the first leg expands within the labyrinth chamber so as to limit an amount of the high-pressure fluid that passes beyond the second leg.
摘要翻译： 迷宫式密封件，其可以包括围绕燕尾形突片的高压侧定位的第一腿部，围绕燕尾形舌片的低压侧定位的第二腿部，以及位于第一腿部和第二腿部之间的迷宫腔室。 通过第一腿周围的间隙的高压流体在迷宫腔内膨胀，以限制超过第二腿的高压流体的量。
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公开(公告)号：US08007246B2
公开(公告)日：2011-08-30
申请号：US11654182
申请日：2007-01-17
申请人： Raymond Grant Rowe , Tara Easter McGovern , Jane Ann Murphy , Andrew Jay Skoog , William R. Stowell , Paul Thomas Marks , Lisa DeBellis , James H. Clare
发明人： Raymond Grant Rowe , Tara Easter McGovern , Jane Ann Murphy , Andrew Jay Skoog , William R. Stowell , Paul Thomas Marks , Lisa DeBellis , James H. Clare
IPC分类号： F01D5/18
CPC分类号： C23C4/02 , F01D5/288 , F05D2230/90 , Y02T50/673
摘要： A method of fabricating a component for a gas turbine engine is provided. The method includes applying a bond coat to at least a portion of the component, applying a dense vertically cracked (DVC) thermal barrier coating to at least a portion of the bond coat using a spray mechanism positioned a first distance from the component, and overlying at least a portion of the DVC thermal barrier coating with a soft coat thermal barrier coating using a spray mechanism that is positioned a second distance away from the component, wherein the second distance is greater than the first distance to facilitate adherence of the soft coating thermal barrier coating to the DVC thermal barrier coating.
摘要翻译： 提供一种制造用于燃气轮机的部件的方法。 该方法包括将粘合涂层施加到部件的至少一部分上，使用位于距部件第一距离的喷涂机构将至少一部分粘合涂层施加致密的垂直裂纹（DVC）热障涂层，并且覆盖 所述DVC热障涂层的至少一部分具有使用喷涂机构的软涂层热障涂层，所述喷涂机构位于远离所述部件的第二距离处，其中所述第二距离大于所述第一距离以促进所述软涂层热粘附 阻隔涂层到DVC隔热涂层。
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公开(公告)号：US20100007092A1
公开(公告)日：2010-01-14
申请号：US12168932
申请日：2008-07-08
IPC分类号： F02F11/00 , F16J15/447
CPC分类号： F01D5/3007 , F01D5/081 , F01D5/087 , F01D11/005 , F01D11/006 , F01D11/02
摘要： A labyrinth seal that may include a first leg positioned about a high-pressure side of the dovetail tab, a second leg positioned about a low-pressure side of the dovetail tab, and a labyrinth chamber positioned between the first leg and the second leg. High-pressure fluid passing through the gap about the first leg expands within the labyrinth chamber so as to limit an amount of the high-pressure fluid that passes beyond the second leg.
摘要翻译： 迷宫式密封件，其可以包括围绕燕尾形突片的高压侧定位的第一腿部，围绕燕尾形舌片的低压侧定位的第二腿部，以及位于第一腿部和第二腿部之间的迷宫腔室。 通过第一腿周围的间隙的高压流体在迷宫腔内膨胀，以限制超过第二腿的高压流体的量。
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公开(公告)号：US07500824B2
公开(公告)日：2009-03-10
申请号：US11507562
申请日：2006-08-22
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F01D11/02
摘要： An abradable seal is provided to improve turbine performance by physically reducing the clearance between a flange portion of the nozzle and an opposed angel wing/seal plate member of the bucket. The provision of an abradable seal also mitigates angel wing/seal plate tooth or fin wear by providing for abradable contact without metal to metal hard rub.
摘要翻译： 提供可磨损密封件以通过物理地减小喷嘴的凸缘部分和铲斗的相对的天使翼/密封板构件之间的间隙来改善涡轮机性能。 提供可磨损的密封件还通过提供无磨损的接触而减轻天使翼/密封板的齿或翅片磨损，而不会金属与金属的硬摩擦。
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公开(公告)号：US07600968B2
公开(公告)日：2009-10-13
申请号：US10907972
申请日：2005-04-22
申请人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter McGovern
发明人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter McGovern
IPC分类号： F01D11/12
CPC分类号： F01D11/12 , F01D11/122
摘要： An article of manufacture pattern for improving aerodynamic performance of a turbine including an abradable material capable of abradable contact. The abradable material is disposed in a pattern. The pattern includes a first plurality of ridges disposed at a base surface of the turbine. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.
摘要翻译： 一种用于改善涡轮机的空气动力性能的制造模式的制品，其包括能够耐磨的接触的耐磨材料。 耐磨材料以图案设置。 该图案包括设置在涡轮机的基面处的第一多个脊。 第一多个脊中的每个脊具有第一侧壁和具有第一端和第二端的第二侧壁。 第一和第二侧壁的第一端从基面延伸。 第一和第二侧壁彼此相对倾斜，具有基本上相等但相反的斜面，直到在相应的第一和第二侧壁的第二端处共同限定脊的中心线和顶部。
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9.发明授权公开(公告)号：US07368164B2
公开(公告)日：2008-05-06
申请号：US10710110
申请日：2004-06-18
申请人： William Randolph Stowell , Daniel Peter Ivkovich , Timothy Lance Manning , Tara Easter McGovern , Jane Ann Murphy , Thomas Walter Rentz , Mathew Curtis Roling , Raymond Grant Rowe , Andrew Jay Skoog
发明人： William Randolph Stowell , Daniel Peter Ivkovich , Timothy Lance Manning , Tara Easter McGovern , Jane Ann Murphy , Thomas Walter Rentz , Mathew Curtis Roling , Raymond Grant Rowe , Andrew Jay Skoog
CPC分类号： C23C24/08 , C23C28/3215 , C23C28/324 , C23C28/345 , C23C28/3455 , Y02T50/67 , Y10T428/252 , Y10T428/256
摘要： A coating and method for overcoating a TBC on a component used in a high-temperature environment, such as the combustor section of an industrial gas turbine. The coating defines the outermost surface of the component and is formed of at least two layers having different compositions. An inner layer of the coating contains alumina in a first silica-containing matrix material that is free of zinc titanate. An outer layer of the coating contains alumina, a glass material, and zinc titanate in a second silica-containing matrix material. The outer layer of the coating has a surface roughness of not greater than three micrometers Ra and forms the outermost surface of the component. The coating reduces the component temperature by reducing the convective and radiant heat transfer thereto.
摘要翻译： 用于在高温环境下使用的部件（例如工业燃气轮机的燃烧器部分）上涂覆TBC的涂层和方法。 该涂层限定了该组件的最外表面，并由至少两层具有不同组成。 涂层的内层在不含钛酸锌的第一含硅基体材料中含有氧化铝。 涂层的外层在第二含硅基体材料中含有氧化铝，玻璃材料和钛酸锌。 涂层的外层具有不大于3微米的Ra的表面粗糙度并形成该组件的最外表面。 涂层通过减少其对流和辐射热传递而降低了组件温度。
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