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    Aluminide or chromide coating of turbine engine rotor component
    1.
    发明授权
    Aluminide or chromide coating of turbine engine rotor component 失效
    涡轮发动机转子部件的铝酸盐或铬酸盐涂层

    公开(公告)号：US06921251B2

    公开(公告)日：2005-07-26

    申请号：US10655835

    申请日：2003-09-05

    申请人： John Frederick Ackerman ,  Michael James Weimer ,  Joseph Aloysius Heaney ,  Robert George Zimmerman, Jr. ,  Bangalore Aswatha Nagaraj ,  Brian Thomas Hazel ,  Nripendra Nath Das

    发明人： John Frederick Ackerman ,  Michael James Weimer ,  Joseph Aloysius Heaney ,  Robert George Zimmerman, Jr. ,  Bangalore Aswatha Nagaraj ,  Brian Thomas Hazel ,  Nripendra Nath Das

    IPC分类号： C23C10/02 ,  C23C16/16 ,  C23C16/20 ,  F01D5/28 ,  F01D5/14

    CPC分类号： F01D5/288 ,  C23C10/02 ,  C23C16/16 ,  C23C16/20 ,  F05D2230/90 ,  F05D2300/611 ,  Y02T50/67

    摘要： A turbine engine rotor component, such as a compressor or turbine disk or seal element, is protected from corrosion by depositing an aluminum or chromium coating on the component. The deposition can be performed by a vapor deposition process, such as metal organic chemical vapor deposition (MOCVD), to a coating thickness of from about 0.2 to about 50 microns, typically from about 0.5 to about 3 microns. In one embodiment, the method is conducted in a vapor coating container having a hollow interior coating chamber, and includes the steps of loading the coating chamber with the component to be coated; and flowing a tri-alkyl aluminum or chromium carbonyl coating gas into the loaded coating chamber at a specified temperature, pressure, and time to deposit an aluminum or chromium coating on the surface of the component. The coated component is then heated in a nonoxidizing atmosphere to a specified temperature to form an aluminide or chromide coating on the surface. The coated component is typically then heated or maintained at an elevated temperature in the presence of oxygen to form an oxide coating on the surface of the component.

    摘要翻译： 诸如压缩机或涡轮盘或密封元件的涡轮发动机转子部件通过在组件上沉积铝或铬涂层来防止腐蚀。 沉积可以通过气相沉积工艺（例如金属有机化学气相沉积（MOCVD））进行，涂层厚度为约0.2至约50微米，通常为约0.5至约3微米。 在一个实施方案中，该方法在具有中空内部涂覆室的蒸气涂覆容器中进行，并且包括以下步骤：将涂覆室与要涂覆的组分装载; 并在规定的温度，压力和时间下将三烷基铝或铬羰基涂覆气体流入装载的涂覆室，以在组件的表面上沉积铝或铬涂层。 然后将涂覆的组分在非氧化气氛中加热至特定温度，以在表面上形成铝化物或铬酸盐涂层。 然后通常在氧存在下将涂覆的组分加热或保持在升高的温度，以在组分的表面上形成氧化物涂层。

    CERAMIC CORROSION RESISTANT COATING FOR OXIDATION RESISTANCE
    2.
    发明申请
    CERAMIC CORROSION RESISTANT COATING FOR OXIDATION RESISTANCE 审中-公开
    陶瓷耐腐蚀涂层耐氧化

    公开(公告)号：US20100279018A1

    公开(公告)日：2010-11-04

    申请号：US12839142

    申请日：2010-07-19

    申请人： Brian Thomas Hazel ,  Jeffrey Pfaendtner ,  Kevin Paul McEvoy ,  Bangalore Aswatha Nagaraj

    发明人： Brian Thomas Hazel ,  Jeffrey Pfaendtner ,  Kevin Paul McEvoy ,  Bangalore Aswatha Nagaraj

    IPC分类号： B05D3/02

    CPC分类号： F01D5/288 ,  C23C18/1208 ,  C23C18/1254 ,  C23C18/1283 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  F05D2300/2118 ,  Y02T50/67 ,  Y02T50/6765 ,  Y10T428/26

    摘要： A coating system and a method for forming the coating system, the method including coating a surface of a gas turbine engine turbine component having a metallic surface that is outside the combustion gas stream and exposed to cooling air during operation of the engine. A gel-forming solution including a ceramic metal oxide precursor is provided. The gel-forming solution is heated to a first preselected temperature for a first preselected time to form a gel. The gel is then deposited on the metallic surface. Thereafter the gel is fired at a second preselected temperature above the first preselected temperature to form a ceramic corrosion resistant coating comprising a ceramic metal oxide is selected from the group consisting of zirconia, hafnia and combinations thereof. The ceramic corrosion resistant coating having a thickness of up to about 127 microns and remaining adherent at temperatures greater than about 1000° F.

    摘要翻译： 一种涂覆系统和一种形成涂层系统的方法，所述方法包括在发动机操作期间涂覆具有在燃烧气流外部的金属表面并暴露于冷却空气的燃气涡轮发动机涡轮机部件的表面。 提供了包含陶瓷金属氧化物前体的凝胶形成溶液。 将凝胶形成溶液加热至第一预选温度第一预选时间以形成凝胶。 然后将凝胶沉积在金属表面上。 此后，凝胶在高于第一预选温度的第二预选温度下烧制以形成陶瓷耐腐蚀涂层，其包含选自氧化锆，铪及其组合的陶瓷金属氧化物。 陶瓷耐腐蚀涂层的厚度高达约127微米，并在大于约1000°F的温度下保持粘附。

    LAYERED CORROSION RESISTANT COATING FOR TURBINE BLADE ENVIRONMENTAL PROTECTION
    6.
    发明申请
    LAYERED CORROSION RESISTANT COATING FOR TURBINE BLADE ENVIRONMENTAL PROTECTION 审中-公开
    用于涡轮叶片环境保护的层状耐腐蚀涂层

    公开(公告)号：US20090047135A1

    公开(公告)日：2009-02-19

    申请号：US11925360

    申请日：2007-10-26

    申请人： Bangalore Aswatha Nagaraj ,  Brian Thomas Hazel

    发明人： Bangalore Aswatha Nagaraj ,  Brian Thomas Hazel

    IPC分类号： F01D5/14

    CPC分类号： C23C24/08 ,  C23C26/00 ,  C23C30/00 ,  F01D5/288 ,  F05D2300/50212 ,  Y02T50/67 ,  Y02T50/671

    摘要： The present invention is a gas turbine engine turbine blade comprising an airfoil section having at least an exterior surface, a platform section having an exterior surface, an under platform section having an exterior surface, and a dovetail section having an exterior surface. The blade further comprises a corrosion resistant coating on a surface of a turbine blade section selected from the group consisting of the exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the corrosion resistant coating comprising a particulate corrosion resistant component comprising from about 5 weight percent to about 100 weight percent corrosion resistant non-alumina particulates having a CTE greater than that of alumina particulates and balance alumina particulates, and a binder component. The present invention also includes methods for making such a gas turbine engine blade.

    摘要翻译： 本发明是一种燃气涡轮发动机涡轮叶片，其包括具有至少外表面的翼型部分，具有外表面的平台部分，具有外表面的下平台部分和具有外表面的燕尾部分。 叶片还包括在涡轮叶片部分的表面上的防腐蚀涂层，其选自下面的平台部分的外表面，燕尾部分的外表面及其组合，耐腐蚀涂层包括颗粒 包含约5重量％至约100重量％的耐腐蚀非氧化铝颗粒的耐蚀性组分，其CTE大于氧化铝颗粒的平均值和余量的氧化铝颗粒，以及粘合剂组分。 本发明还包括制造这种燃气涡轮发动机叶片的方法。

    Thermal/environmental barrier coating system for silicon-containing materials
    7.
    发明授权
    Thermal/environmental barrier coating system for silicon-containing materials 有权
    含硅材料的热/环境屏障涂层系统

    公开(公告)号：US07407718B2

    公开(公告)日：2008-08-05

    申请号：US11160185

    申请日：2005-06-13

    申请人： Brian Thomas Hazel ,  Irene Spitsberg ,  Christine Govern ,  Bangalore Aswatha Nagaraj

    发明人： Brian Thomas Hazel ,  Irene Spitsberg ,  Christine Govern ,  Bangalore Aswatha Nagaraj

    IPC分类号： B32B9/00

    CPC分类号： C23C28/04 ,  C04B41/009 ,  C04B41/52 ,  C04B41/89 ,  F01D5/284 ,  F01D5/288 ,  Y10T428/12576 ,  C04B41/4527 ,  C04B41/5096 ,  C04B41/5037 ,  C04B41/5024 ,  C04B41/5031 ,  C04B41/5044 ,  C04B41/5042 ,  C04B41/4529 ,  C04B41/522 ,  C04B35/565 ,  C04B35/584 ,  C04B35/806

    摘要： A coating system for Si-containing materials, particularly Si-based composites used to produce articles exposed to high temperatures. The coating system is a compositionally-graded thermal/environmental barrier coating (T/EBC) system that includes an intermediate layer containing yttria-stabilized hafnia (YSHf) and mullite, alumina and/or an aluminosilicate, which is used in combination with an inner layer between a Si-containing substrate and the intermediate layer and a thermal-insulating top coat overlying the intermediate layer. The intermediate layer provides environmental protection to the silicon-containing substrate, and has a coefficient of thermal expansion between that of the top coat and that of the inner layer so as to serve as a transition layer therebetween. The intermediate layer is particular well suited for use in combination with an inner layer of an alkaline earth metal aluminosilicate (such as BSAS) and a top coat formed of YSZ or YSHf.

    摘要翻译： 用于含Si材料的涂层系统，特别是用于生产暴露于高温的制品的Si基复合材料。 涂层系统是一种组成分级的热/环境屏障涂层（T / EBC）系统，其包括含有氧化钇稳定的铪（YSHf）和莫来石，氧化铝和/或铝硅酸盐的中间层，其与内部 在含Si衬底和中间层之间的层和覆盖中间层的绝热顶涂层。 中间层为含硅基材提供环境保护，并且具有顶涂层与内层层之间的热膨胀系数，以便在其间作为过渡层。 中间层特别适用于与碱土金属硅铝酸盐（如BSAS）的内层和由YSZ或YSHf形成的顶层组合使用。

    Layered paint coating for turbine blade environmental protection
    8.
    发明授权
    Layered paint coating for turbine blade environmental protection 有权
    涡轮叶片环保涂层涂层

    公开(公告)号：US07311940B2

    公开(公告)日：2007-12-25

    申请号：US11266857

    申请日：2005-11-04

    申请人： Bangalore Aswatha Nagaraj ,  Brian Thomas Hazel

    发明人： Bangalore Aswatha Nagaraj ,  Brian Thomas Hazel

    IPC分类号： B05D1/12 ,  B05D1/32 ,  B05D1/38

    CPC分类号： C23C24/08 ,  C23C26/00 ,  C23C30/00 ,  F01D5/288 ,  F05D2300/50212 ,  Y02T50/67 ,  Y02T50/671

    摘要： The present invention is a gas turbine engine turbine blade comprising an airfoil section having at least an exterior surface, a platform section having an exterior surface, an under platform section having an exterior surface, and a dovetail section having an exterior surface. The blade further comprises a corrosion resistant coating on a surface of a turbine blade section selected from the group consisting of the exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the corrosion resistant coating comprising a particulate corrosion resistant component comprising from about 5 weight percent to about 100 weight percent corrosion resistant non-alumina particulates having a CTE greater than that of alumina particulates and balance alumina particulates, and a binder component. The present invention also includes methods for making such a gas turbine engine blade.

    摘要翻译： 本发明是一种燃气涡轮发动机涡轮叶片，其包括具有至少外表面的翼型部分，具有外表面的平台部分，具有外表面的下平台部分和具有外表面的燕尾部分。 叶片还包括在涡轮叶片部分的表面上的抗腐蚀涂层，其选自下部平台部分的外表面，燕尾部分的外表面及其组合，耐腐蚀涂层包括颗粒 包含约5重量％至约100重量％的耐腐蚀非氧化铝颗粒的耐蚀性组分，其CTE大于氧化铝颗粒的平均值和余量的氧化铝颗粒，以及粘合剂组分。 本发明还包括制造这种燃气涡轮发动机叶片的方法。