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公开(公告)号：US07556695B2
公开(公告)日：2009-07-07
申请号：US10140343
申请日：2002-05-06
IPC分类号： C23C16/00
摘要： Methods and apparatus to make multilayer thermal barrier coatings for superalloy substrates such as turbine blades or vanes are disclosed. The methods produce non-homogeneous, nanometer-size, successive layers and a non-homogeneous interfacial layer without the use of baffles. Methods are also disclosed to use a lower cost metallic source and an oxygen bleed to create alumina or tantalum oxide vapor, to use a tantalum oxide or an alumina ingot and a low pressure inert gas feed to direct the vapor clouds, to use pulsed evaporation from a secondary vapor source to create non-homogeneous multilayer coating on non-rotated substrates, to use an electric bias to direct the vapor clouds, and to use a mechanical system to direct the vapor clouds or move and position the article to be coated in the clouds.
摘要翻译： 公开了用于制造用于超级合金基底（例如涡轮叶片或叶片）的多层热障涂层的方法和装置。 该方法不使用挡板产生非均匀，纳米尺寸，连续层和非均匀界面层。 还公开了使用较低成本的金属源和氧气渗出物以产生氧化铝或氧化钽蒸汽的方法，以使用氧化钽或氧化铝锭和低压惰性气体进料来引导蒸汽云，以使用脉冲蒸发 二次蒸汽源，以在非旋转基板上产生非均匀的多层涂层，以使用电偏压来引导蒸气云，并且使用机械系统引导蒸汽云或移动和定位待涂覆的制品 云彩
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22.发明授权公开(公告)号：US07416788B2
公开(公告)日：2008-08-26
申请号：US11170836
申请日：2005-06-30
IPC分类号： B32B9/00
CPC分类号： F01D5/288 , C04B35/486 , C04B2235/3251 , C04B2235/762 , C04B2235/765 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , F05D2230/313 , F05D2230/90 , F05D2300/2285 , F05D2300/611 , Y02T50/67 , Y02T50/671 , Y02T50/673
摘要： A turbine engine component includes an electron beam-physical vapor deposition thermal barrier coating covering at least a portion of a substrate. The thermal barrier coating includes an inner layer having a columnar-grained microstructure with inter-columnar gap porosity. The inner layer includes a stabilized ceramic material. The thermal barrier coating also includes a substantially non-porous outer layer, covering the inner layer and including the stabilized ceramic material. The outer layer is deposited with continuous line-of-sight exposure to the vapor source under oxygen deficient conditions. The outer layer may further comprise a dopant oxide that is more readily reducible than the stabilized ceramic material. During deposition, the outer layer may also have an oxygen deficient stoichiometry with respect to the inner layer. Oxygen stoichiometry in the outer layer may be restored by exposure of the coated component to an oxidizing environment.
摘要翻译： 涡轮发动机部件包括覆盖基板的至少一部分的电子束物理气相沉积热障涂层。 隔热涂层包括具有柱状间隙孔隙的柱状微结构的内层。 内层包括稳定的陶瓷材料。 热障涂层还包括基本上无孔的外层，覆盖内层并且包括稳定的陶瓷材料。 在缺氧条件下，外层沉积有连续的视线暴露于蒸汽源。 外层还可以包含比稳定的陶瓷材料更容易还原的掺杂剂氧化物。 在沉积期间，外层也可能具有相对于内层的缺氧化学计量。 可以通过将涂覆的组分暴露于氧化环境来恢复外层中的氧化学计量。
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公开(公告)号：US20080166225A1
公开(公告)日：2008-07-10
申请号：US11227780
申请日：2005-09-14
IPC分类号： F01D5/20
CPC分类号： F01D11/122 , C23C26/02 , C23C28/321 , C23C28/3215 , C23C28/324 , C23C28/345 , C23C28/3455 , C23C30/00 , F01D5/20 , F05D2300/21 , F05D2300/2118
摘要： A turbine blade tip and shroud clearance control coating system comprising an abrasive blade tip coating and an abradable shroud coating are provided. The abrasive layer may comprise abrasive particles of cubic zirconia, cubic hafnia or mixtures thereof, and the abradable layer may be a nanolaminate thermal barrier coating that is softer than the abrasive layer. The invention further provides an alternate coating system comprising an abradable blade tip coating and an abrasive shroud coating.
摘要翻译： 提供了一种涡轮叶片尖端和护罩间隙控制涂层系统，其包括研磨刀片涂层和可磨损的护罩涂层。 研磨层可以包括立方氧化锆，立方铪或其混合物的磨料颗粒，并且可磨损层可以是比磨料层软的纳米级隔热涂层。 本发明还提供了一种替代涂层系统，其包括可磨损的刀片末端涂层和磨料罩涂层。
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公开(公告)号：US07282271B2
公开(公告)日：2007-10-16
申请号：US11000743
申请日：2004-12-01
CPC分类号： C23C26/00 , C23C28/321 , C23C28/345 , C23C28/3455 , Y02T50/67
摘要： A durable protective coating may be formed by applying a thin layer of metastable alumina to a bond coating on a substrate. A thermal barrier coating may then be applied to the metastable alumina and the resulting part may be heat treated to transform the metastable alumina to a mixed alpha alumina having particles of the thermal barrier coating, such as zirconia in the case of an yttria stabilized zirconia thermal barrier coating, dispersed therein. The resulting thermal barrier coating may inhibit microbuckling of the thermally grown oxide scale that grows over time at the thermal barrier coating-bond coating interface.
摘要翻译： 可以通过将薄的亚稳态氧化铝涂覆在基底上的粘结涂层上来形成持久的保护涂层。 然后可以将热障涂层施加到亚稳态氧化铝上，并且所得到的部分可以被热处理以将亚稳态氧化铝转变成具有热障涂层颗粒的混合α氧化铝，例如在氧化钇稳定的氧化锆热的情况下的氧化锆 阻隔涂层，分散在其中。 所得到的热障涂层可以抑制在热障涂层 - 结合涂层界面处随时间增长的热生长氧化皮的微珠。
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公开(公告)号：US06482537B1
公开(公告)日：2002-11-19
申请号：US09535394
申请日：2000-03-24
IPC分类号： B32B514
CPC分类号： C23C28/3215 , C23C28/345 , C23C28/3455 , C23C28/36 , Y10T428/12458 , Y10T428/12479 , Y10T428/12549 , Y10T428/12576 , Y10T428/12611 , Y10T428/12618
摘要： A thermal barrier coating for superalloy articles such as turbine engine vanes and blades that are exposed to high temperature gas is disclosed. The coating includes a columnar grained ceramic layer applied to an aluminide or MCrAlY bond coat by electron beam physical vapor deposition. The ceramic layer is comprised a plurality of layers of zirconia stabilized with 20 percent yttria and the interfaces between the layers are decorated with particles selected from a group consisting of Ta2O5 and alumina. Though not essential to the invention a layer of tetragonal zirconia may be deposited both under and over the ceramic coat. An improved electron physical beam vapor deposition process for applying this ceramic layer is also disclosed.
摘要翻译： 公开了用于暴露于高温气体的超级合金制品例如涡轮发动机叶片和叶片的隔热涂层。 涂层包括通过电子束物理气相沉积施加到铝化物或MCrAlY键合层的柱状晶粒陶瓷层。 陶瓷层由多层用20％氧化钇稳定的氧化锆层组成，层间的界面用选自Ta2O5和氧化铝的颗粒进行装饰。 尽管对本发明不是必需的，但在陶瓷涂层的下方和上方可沉积一层四方晶氧化锆。 还公开了一种用于施加该陶瓷层的改进的电子物理气相沉积工艺。
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公开(公告)号：US6103386A
公开(公告)日：2000-08-15
申请号：US944391
申请日：1997-10-06
CPC分类号： C23C28/3215 , C23C28/00 , C23C28/345 , C23C28/3455 , F01D5/288 , F05D2300/21 , F05D2300/2112 , F05D2300/2118 , F05D2300/5024
摘要： A thermal barrier coating for superalloy turbine engine vanes and blades that are exposed to high temperature gas is disclosed. The coating includes an aluminide or MCrAlY layer, an alumina layer, and a ceramic top layer. The ceramic layer has a columnar grain microstructure. A bond inhibitor is disposed in the gaps between the columnar grains. This inhibitor is preferably alumina.
摘要翻译： 公开了暴露于高温气体的超级合金涡轮发动机叶片和叶片的隔热涂层。 涂层包括铝化物或MCrAlY层，氧化铝层和陶瓷顶层。 陶瓷层具有柱状晶粒微观结构。 键合抑制剂设置在柱状晶粒之间的间隙中。 该抑制剂优选为氧化铝。
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公开(公告)号：US09738533B2
公开(公告)日：2017-08-22
申请号：US12969390
申请日：2010-12-15
申请人： Derek Raybould , Christian Delacruz , Carl Kiser
发明人： Derek Raybould , Christian Delacruz , Carl Kiser
CPC分类号： C01B33/12 , C01B33/14 , C23C18/1216 , C23C18/1254 , C23C18/1283 , C23C18/1295
摘要： A coating for spark plugs and engine parts is resistant to fouling. The coating may be applied to the spark plug or engine part by dipping the part in a sol gel solution, ensuring it wets the part, and extracting it at a slow, controlled rate. As the part is allowed to dry, the sol gel reacts with moisture in the air to form a thin oxide film. Unlike conventional sol gel applications, which apply the oxide directly to the part, the present invention may form an oxide coating, in situ, while drying in place on the part.
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28.发明申请PROTECTIVE COATING SYSTEMS FOR GAS TURBINE ENGINE APPLICATIONS AND METHODS FOR FABRICATING THE SAME 审中-公开气体涡轮发动机用保护涂层系统及其制造方法公开(公告)号：US20110305921A1
公开(公告)日：2011-12-15
申请号：US13173075
申请日：2011-06-30
CPC分类号： C23C30/00 , C23C18/1208 , C23C18/1216 , C23C18/1225 , C23C18/1229 , C23C18/1254 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , F01D5/288 , F05D2230/31 , F05D2300/611 , Y10T428/12611
摘要： Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary protective coating system comprises an aluminide-comprising bond coating disposed on a substrate, a thermal barrier coating overlying the aluminide-comprising bond coating, and a silicate layer interposed between the thermal barrier coating and the aluminide-comprising bond coating.
摘要翻译： 提供了用于燃气涡轮发动机应用的保护涂层系统以及用于制造这种保护涂层系统的方法。 示例性保护涂层系统包括设置在基底上的含铝化物粘合涂层，覆盖所述含铝化物粘合涂层的热障涂层以及置于所述热障涂层和所述含铝化物粘合涂层之间的硅酸盐层。
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公开(公告)号：US07479299B2
公开(公告)日：2009-01-20
申请号：US11044873
申请日：2005-01-26
申请人： Derek Raybould , Murali N. Madhava
发明人： Derek Raybould , Murali N. Madhava
IPC分类号： B05D1/02
CPC分类号： C23C24/04 , Y10T428/12181
摘要： The present invention thus provides an improved method for coating turbine engine components. The method utilizes a cold high velocity gas spray technique to coat turbine blades, compressor blades, impellers, blisks, and other turbine engine components. These methods can be used to coat a variety of surfaces thereon, thus improving the overall durability, reliability and performance of the turbine engine itself. The method includes the deposition of powders of alloys of nickel and aluminum wherein the powders are formed so as to have an amorphous microstructure. Layers of the alloys may be deposited and built up by cold high velocity gas spraying. The coated items displayed improved characteristics such as hardness, strength, and corrosion resistance.
摘要翻译： 因此，本发明提供了一种用于涂覆涡轮发动机部件的改进方法。 该方法利用冷高速气体喷射技术来涂覆涡轮叶片，压缩机叶片，叶轮，叶片和其它涡轮发动机部件。 这些方法可用于在其上涂覆各种表面，从而提高涡轮发动机本身的整体耐久性，可靠性和性能。 该方法包括沉积镍和铝的合金粉末，其中形成粉末以具有无定形微结构。 可以通过冷高速气体喷涂沉积和堆积合金层。 涂层物品显示出改善的特性，如硬度，强度和耐腐蚀性。
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公开(公告)号：US07455881B2
公开(公告)日：2008-11-25
申请号：US11114470
申请日：2005-04-25
IPC分类号： B05D1/02
CPC分类号： C23C24/04
摘要： The present invention provides methods and materials for use in applying a coating on a surface of a magnesium component. The method includes the steps of: accelerating a coating powder to a velocity of between about 500 to about 1200 meters/second, wherein the coating powder comprises a material selected from the group consisting of aluminum, aluminum alloys, titanium, titanium alloys, and composites; directing the coating powder through a convergent-divergent nozzle onto the surface of the magnesium component; and forming a coating on the surface of the magnesium component so as to substantially cover the surface of the magnesium component. The coating thickness may be between approximately 0.1 to approximately 1.0 mm.
摘要翻译： 本发明提供了用于在镁组分的表面上施加涂层的方法和材料。 该方法包括以下步骤：将涂层粉末加速至约500至约1200米/秒的速度，其中涂层粉末包括选自铝，铝合金，钛，钛合金和复合材料的材料 ; 将涂层粉末通过会聚扩散喷嘴引导到镁组分的表面上; 并在镁组分的表面上形成涂层，以便基本上覆盖镁组分的表面。 涂层厚度可以在约0.1至约1.0mm之间。
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