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    Multi-layer thermal barrier coating with transpiration cooling
    4.
    发明授权
    Multi-layer thermal barrier coating with transpiration cooling 失效
    蒸发冷却多层隔热涂层

    公开(公告)号：US06511762B1

    公开(公告)日：2003-01-28

    申请号：US09707024

    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： F01D5/288 ,  B32B18/00 ,  B32B2311/22 ,  C04B35/111 ,  C04B35/486 ,  C04B35/488 ,  C04B37/026 ,  C04B2235/3225 ,  C04B2235/402 ,  C04B2235/404 ,  C04B2237/123 ,  C04B2237/125 ,  C04B2237/405 ,  C04B2237/62 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  C23C28/36 ,  F01D5/183 ,  F05D2260/203 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T428/12611 ,  Y10T428/24273 ,  Y10T428/24289 ,  Y10T428/24347 ,  Y10T428/24992 ,  Y10T428/249953 ,  Y10T428/249956 ,  Y10T428/24996

    摘要： A cooling system for cooling of the flow path surface region of an engine component used in a gas turbine engine and a method for making a system for cooling of the flow path surface region of an engine component used in a gas turbine engine. The method comprises the steps of channeling apertures in a substrate to a diameter of about 0.0005″ to about 0.02″ to allow passage of cooling fluid from a cooling fluid source; applying a bond coat of about 0.0005″ to about 0.005″ in thickness to the substrate such that the bond coat partially fills the channels; applying a porous inner TBC layer of at least about 0.01″ in thickness to the bond coat, such that the TBC fills the channels; applying an intermediate ceramic layer that is more dense than the inner TBC layer on top of the porous TBC; applying an outer TBC layer over the intermediate layer; and, passing cooling fluid from a cooling fluid source through the channel into the porous TBC. The density of the outer TBC layer can be varied as needed to achieve desired cooling objectives. Because the channel exit is filled with porous TBC material, cooling fluid flows through the porous passageways into the inner TBC layer. Although the passageways provide a plurality of tortuous routes, the increased density of the TBC in the intermediate layer provides a resistance to flow of the cooling fluid and effectively causes the cooling fluid to more efficiently spread through the TBC in the inner layer before exiting at the outer surface.

    摘要翻译： 一种用于冷却燃气涡轮发动机中使用的发动机部件的流路表面区域的冷却系统和用于制造用于燃气涡轮发动机的发动机部件的流路面区域的系统的方法。 该方法包括以下步骤：将衬底中的孔引导至约0.0005“至约0.02”的直径，以允许冷却流体从冷却流体源通过; 对基底施加厚度为约0.0005“至约0.005”的粘结层，使得粘结涂层部分填充通道; 将至少约0.01“的厚度的多孔内部TBC层施加到粘合涂层，使得TBC填充通道; 在多孔TBC的顶部施加比内部TBC层更致密的中间陶瓷层; 在所述中间层上施加外部TBC层; 并且将来自冷却流体源的冷却流体通过通道进入多孔TBC。 可以根据需要改变外部TBC层的密度以实现所需的冷却目标。 由于通道出口填充有多孔TBC材料，冷却流体流过多孔通道进入内部TBC层。 虽然通道提供了多条曲折的路线，但是TBC在中间层中的增加的密度提供了对冷却流体的流动的阻力，并有效地使冷却流体在内层中更加有效地扩散通过TBC， 外表面。

    Cooled thermal barrier coating on a turbine blade tip
    5.
    发明授权
    Cooled thermal barrier coating on a turbine blade tip 有权
    在涡轮叶片尖端上的冷却的热障涂层

    公开(公告)号：US06461108B1

    公开(公告)日：2002-10-08

    申请号：US09818384

    申请日：2001-03-27

    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： F01D518

    CPC分类号： F01D5/182 ,  C23C28/00 ,  F01D5/183 ,  F01D5/20 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49318

    摘要： A cooling system for cooling of the squealer tip surface region of a high pressure turbine blade used in a gas turbine engine and a method for making a system for cooling of the squealer tip surface region of a high pressure turbine blade used in a gas turbine engine. The method comprises the steps of channeling apertures in a tip cap to a diameter of about 0.004″ to about 0.020″ to allow passage of cooling fluid from a cooling fluid source; applying a bond coat of about 0.0005″ to about 0.010″ in thickness to the tip cap such that the bond coat partially fills the channels; applying a porous TBC layer of at least about 0.003″ in thickness to the bond coat, such that the porous TBC fills the channels; applying a dense ceramic TBC layer over the porous layer; and, passing cooling fluid from a cooling fluid source through the channel into the porous TBC. The density of the dense TBC layer can be varied as needed to achieve desired cooling objectives. Because the channel exit is filled with porous TBC material, cooling fluid flows through the porous passageways in the porous TBC layer into the squealer tip. Although the passageways provide a plurality of tortuous routes, the increased density of the TBC in the dense ceramic layer provides a resistance to flow of the cooling fluid and effectively causes the cooling fluid to more efficiently spread through the TBC into the squealer tip before exiting into the gas stream at the outer surface.

    摘要翻译： 一种用于冷却燃气涡轮发动机中使用的高压涡轮机叶片的鸣响器尖端表面区域的冷却系统以及用于冷却燃气涡轮发动机中使用的高压涡轮机叶片的鸣叫器尖端表面区域的系统的方法 。 该方法包括以下步骤：将顶盖中的孔引导至约0.004“至约0.020”的直径，以允许冷却流体从冷却流体源通过; 对顶盖施加厚度为约0.0005“至约0.010”的粘结层，使得粘结涂层部分填充通道; 将至少约0.003“的多孔TBC层施加到粘结涂层，使得多孔TBC填充通道; 在多孔层上施加致密的陶瓷TBC层; 并且将来自冷却流体源的冷却流体通过通道进入多孔TBC。 可以根据需要改变致密TBC层的密度以实现期望的冷却目标。 由于通道出口填充有多孔TBC材料，所以冷却流体流过多孔TBC层中的多孔通道进入到尖叫尖端。 尽管通道提供了多条曲折的路径，但是致密陶瓷层中TBC的增加的密度提供了对冷却流体的流动的阻力，并且有效地使冷却流体更有效地通过TBC传播到鸣叫器尖端中，然后退出 在外表面的气流。

    Process for forming thermal barrier coating resistant to infiltration
    6.
    发明授权
    Process for forming thermal barrier coating resistant to infiltration 有权
    形成防渗涂层的方法

    公开(公告)号：US07807231B2

    公开(公告)日：2010-10-05

    申请号：US11164615

    申请日：2005-11-30

    申请人： Mark Daniel Gorman ,  Bangalore Aswatha Nagaraj ,  Robert Edward Schafrik

    发明人： Mark Daniel Gorman ,  Bangalore Aswatha Nagaraj ,  Robert Edward Schafrik

    IPC分类号： H05H1/24 ,  B05D3/06 ,  B05D5/00 ,  B05D3/04 ,  B05D3/02 ,  B05D3/14

    CPC分类号： C23C4/18 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  F01D5/288 ,  F05D2230/40

    摘要： A process for protecting a thermal barrier coating (TBC) on a component used in a high-temperature environment, such as the hot section of a gas turbine engine. The process applies a protective film on the surface of the TBC to resist infiltration of contaminants such as CMAS that can melt and infiltrate the TBC to cause spallation. The process generally entails applying to the TBC surface a metal composition containing at least one metal whose oxide resists infiltration of CMAS into the TBC. The metal composition is applied so as to form a metal film on the TBC surface and optionally to infiltrate porosity within the TBC beneath its surface. The metal composition is then converted to form an oxide film, with at least a portion of the oxide film forming a surface deposit on the TBC surface.

    摘要翻译： 一种用于在诸如燃气涡轮发动机的热部分的高温环境中使用的部件上保护热障涂层（TBC）的方法。 该方法在TBC的表面上施加保护膜以防止可能熔化和渗透TBC的污染物诸如CMAS的污染物渗透以引起剥落。 该方法通常需要向TBC表面施加含有至少一种金属的金属组合物，该金属的氧化物抵抗CMAS渗透到TBC中。 施加金属组合物以在TBC表面上形成金属膜，并且任选地在其表面下方的TBC内渗透孔隙。 然后将金属组合物转化成氧化物膜，其中至少一部分氧化膜在TBC表面上形成表面沉积物。

    Directly cooled thermal barrier coating system
    10.
    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。