利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

195 条记录 (耗时 0.026 秒)

    METHOD FOR REPAIRING COATED COMPONENTS USING NIAL BOND COATS
    61.
    发明申请
    METHOD FOR REPAIRING COATED COMPONENTS USING NIAL BOND COATS 有权
    使用NIAL BOND COATS修复涂层组件的方法

    公开(公告)号：US20060029723A1

    公开(公告)日：2006-02-09

    申请号：US10714430

    申请日：2003-11-13

    申请人： Joseph Rigney ,  Ching-Pang Lee ,  Ramgopal Darolia

    发明人： Joseph Rigney ,  Ching-Pang Lee ,  Ramgopal Darolia

    IPC分类号： C23C16/52 ,  B05D3/00

    CPC分类号： B23P6/002 ,  C23C10/02 ,  C23C10/60 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/36 ,  C25D3/50 ,  C25D7/00 ,  C25D7/008 ,  F05B2230/31 ,  F05B2230/90 ,  F05C2253/12

    摘要： According to an embodiment of the invention, a method for repairing a coated high pressure turbine blade, which has been exposed to engine operation, to restore coated airfoil contour dimensions of the blade, and improve upon the prior bond coat is disclosed. The method comprises providing an engine run high pressure turbine blade including a base metal substrate made of a nickel-based alloy and having thereon a thermal barrier coating system. The thermal barrier coating system comprises a diffusion bond coat on the base metal substrate and a top ceramic thermal barrier coating comprising a yttria stabilized zirconia material. The top ceramic thermal barrier coating has a nominal thickness t. The method further comprises removing the thermal barrier coating system, wherein a portion of the base metal substrate also is removed, and determining the thickness of the base metal substrate removed. The portion of the base metal substrate removed has a thickness, Δt. The method also comprises applying a β phase NiAl overlay coating to the substrate, and determining the difference in thickness, Δx, between the β phase NiAl overlay coating and the previously removed bond coat. The method further comprises reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt-Δx, wherein Δt compensates for the portion of removed base metal substrate. Advantageously, the coated airfoil contour dimensions of the high pressure turbine blade are restored to about the coated dimensions preceding the engine run.

    摘要翻译： 根据本发明的实施例，公开了一种已经暴露于发动机操作的用于修复涂覆的高压涡轮机叶片以恢复叶片的被覆翼型轮廓尺寸并改进先前的粘结涂层的方法。 该方法包括提供一种发动机运行的高压涡轮叶片，其包括由镍基合金制成的基底金属基底并且具有热障涂层系统。 热障涂层系统包括在基底金属基底上的扩散粘合涂层和包含氧化钇稳定的氧化锆材料的顶部陶瓷热障涂层。 顶部陶瓷热障涂层具有标称厚度t。 该方法还包括去除热障涂层系统，其中基底金属衬底的一部分也被去除，并且确定移除的母体金属衬底的厚度。 去除的贱金属基材的部分厚度为Deltat。 该方法还包括将β相NiAl覆盖涂层施加到基底上，并确定β相NiAl覆盖涂层与先前去除的粘结涂层之间的厚度差异Deltax。 该方法还包括将顶部陶瓷热障涂层重新施加到t + Deltat-Deltax的标称厚度，其中Deltat补偿去除的基底金属基底的部分。 有利地，高压涡轮机叶片的被覆翼型轮廓尺寸恢复到发动机运行之前的涂层尺寸。

    THERMAL BARRIER COATING SYSTEM
    64.
    发明申请
    THERMAL BARRIER COATING SYSTEM 有权
    热障涂层系统

    公开(公告)号：US20050170200A1

    公开(公告)日：2005-08-04

    申请号：US10708020

    申请日：2004-02-03

    申请人： Bangalore Nagaraj ,  Ramgopal Darolia

    发明人： Bangalore Nagaraj ,  Ramgopal Darolia

    IPC分类号： B32B15/04

    CPC分类号： C23C28/36 ,  C23C4/073 ,  C23C4/10 ,  C23C4/134 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  Y02T50/67 ,  Y10T428/1259 ,  Y10T428/12611 ,  Y10T428/12618

    摘要： A TBC system suitable for protecting the surface of a substrate subjected to a hostile thermal environment. The TBC system comprises a bond coat on the substrate surface, an alumina scale on the bond coat, and a multilayer TBC comprising a thermal-sprayed first ceramic layer on the alumina scale and a thermal-sprayed second ceramic layer overlying the first ceramic layer. The first ceramic layer consists essentially of partially stabilized zirconia so as to comprise the tetragonal and cubic phases of zirconia. The second ceramic layer consists essentially of fully stabilized zirconia so as to consist essentially of the cubic phase of zirconia. The second ceramic layer is also characterized by having vertical microcracks that extend through the thickness thereof. The second ceramic layer is thicker and more erosion resistant than the first ceramic layer.

    摘要翻译： 适用于保护受到恶劣热环境的基板表面的TBC系统。 所述TBC系统包括在所述基材表面上的粘合涂层，所述粘结涂层上的氧化铝垢，以及在所述氧化铝垢上包含热喷涂的第一陶瓷层的多层TBC和覆盖所述第一陶瓷层的热喷涂的第二陶瓷层。 第一陶瓷层基本上由部分稳定的氧化锆组成，以便包含氧化锆的四方晶相和立方相。 第二陶瓷层基本上由完全稳定的氧化锆组成，以便基本上由立方相的氧化锆组成。 第二陶瓷层的特征在于具有延伸穿过其厚度的垂直微裂纹。 第二陶瓷层比第一陶瓷层更厚并且更耐腐蚀。

    Method for repairing coated components
    66.
    发明申请
    Method for repairing coated components 有权
    修复涂层部件的方法

    公开(公告)号：US20050106316A1

    公开(公告)日：2005-05-19

    申请号：US10714213

    申请日：2003-11-13

    申请人： Joseph Rigney ,  Ching-Pang Lee ,  Ramgopal Darolia

    发明人： Joseph Rigney ,  Ching-Pang Lee ,  Ramgopal Darolia

    IPC分类号： B23P6/00 ,  C23C26/00 ,  C23C28/00 ,  F01D5/00 ,  F01D5/14 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00 ,  B32B35/00

    CPC分类号： C23C28/321 ,  C23C26/00 ,  C23C28/325 ,  C23C28/3455 ,  F01D5/005 ,  F01D5/288 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/501 ,  Y10T29/49318

    摘要： According to an embodiment of the invention, a method for repairing a coated high pressure turbine blade, which has been exposed to engine operation, to restore coated airfoil contour dimensions of the blade, is disclosed. The method comprises providing an engine run high pressure turbine blade including a base metal substrate made of a nickel-based alloy and having thereon a thermal barrier coating system. The thermal barrier coating system comprises a diffusion bond coat on the base metal substrate and a top ceramic thermal barrier coating comprising a yttria stabilized zirconia material. The top ceramic thermal barrier coating has a nominal thickness t. The method further comprises removing the thermal barrier coating system, wherein a portion of the base metal substrate also is removed, and determining the thickness of the base metal substrate removed. The portion of the base metal substrate removed has a thickness, Δt. The method also comprises reapplying the diffusion bond coat to the substrate, wherein the bond coat is reapplied to a thickness, which is about the same as applied prior to the engine operation; and reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt, wherein Δt compensates for the portion of removed base metal substrate. Advantageously, the coated airfoil contour dimensions of the high pressure turbine blade are restored to about the coated dimensions preceding the engine run.

    摘要翻译： 根据本发明的实施例，公开了一种已经暴露于发动机操作的用于修复涂覆的高压涡轮机叶片以恢复叶片的被覆翼型轮廓尺寸的方法。 该方法包括提供一种发动机运行的高压涡轮叶片，其包括由镍基合金制成的基底金属基底并且具有热障涂层系统。 热障涂层系统包括在基底金属基底上的扩散粘合涂层和包含氧化钇稳定的氧化锆材料的顶部陶瓷热障涂层。 顶部陶瓷热障涂层具有标称厚度t。 该方法还包括去除热障涂层系统，其中基底金属衬底的一部分也被去除，并且确定移除的母体金属衬底的厚度。 去除的贱金属基材的部分厚度为Deltat。 该方法还包括将扩散粘合涂层重新施加到基底上，其中粘结涂层重新施加到与发动机操作前相同的厚度; 并将顶部陶瓷热障涂层重新施加到标称厚度t + Deltat，其中Deltat补偿去除的基底金属基底的部分。 有利地，高压涡轮机叶片的被覆翼型轮廓尺寸恢复到发动机运行之前的涂层尺寸。

    Directly cooled thermal barrier coating system
    68.
    发明授权
    Directly cooled thermal barrier coating system 失效
    直接冷却热障涂层系统

    公开(公告)号：US06617003B1

    公开(公告)日：2003-09-09

    申请号：US09707023

    申请日：2000-11-06

    申请人： Ching-Pang Lee ,  Robert Edward Schafrik ,  Ramgopal Darolia

    发明人： Ching-Pang Lee ,  Robert Edward Schafrik ,  Ramgopal Darolia

    IPC分类号： B32B1504

    CPC分类号： C23C28/3215 ,  C23C28/321 ,  C23C28/325 ,  C23C28/3455 ,  F01D5/182 ,  F01D5/187 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T428/12611 ,  Y10T428/12736 ,  Y10T428/12944 ,  Y10T428/24273 ,  Y10T428/24289 ,  Y10T428/24298 ,  Y10T428/24306

    摘要： An actively cooled TBC bond coat wherein active convection cooling is provided through micro channels inside or adjacent to a bond coat layer applied to a substrate. The micro channels communicate directly with at least one cooling fluid supply contained within a turbine engine component, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate is covered with an actively cooled bond coat layer, it will reduce the cooling requirement for the substrate, thus allowing the engine to run at higher operating temperature without the need for additional cooling air, achieving a better engine performance. In one form, the component includes a substrate having at least one substrate channel with a first and second end. At least one micro channel is in fluid communication with a plenum which in turn is in fluid communication with at least one substrate channel through an exit orifice in the substrate channel which is at a first end of the substrate channel. A second end of the substrate channel is in communication with a cooling fluid supply, for example, cooling circuits contained within the turbine engine component. The micro channel is located between the substrate surface and the outer gas flow path surface of the component.

    摘要翻译： 主动冷却的TBC粘合涂层，其中主动对流冷却通过施加到基底的粘合涂层的内部或附近的微通道提供。 微通道与包含在涡轮发动机部件内的至少一个冷却流体供应件直接连通，从而为粘合涂层提供直接和有效的冷却。 由于衬底被主动冷却的粘合涂层覆盖，所以它将降低衬底的冷却要求，从而允许发动机在更高的工作温度下运行，而不需要额外的冷却空气，实现更好的发动机性能。 在一种形式中，组件包括具有至少一个具有第一和第二端的衬底通道的衬底。 至少一个微通道与气室流体连通，该气室又与通过基板通道中位于衬底通道的第一端处的出口孔与至少一个衬底通道流体连通。 衬底通道的第二端与冷却流体供应源连通，例如包含在涡轮发动机部件内的冷却回路。 微通道位于基板表面和部件的外部气体流动通道表面之间。