公开(公告)号：US06326057B1

公开(公告)日：2001-12-04

申请号：US09474549

申请日：1999-12-29

申请人： Nripendra N. Das ,  Thomas E. Mantkowski ,  Jackie L. King ,  Floyd A. Swigert ,  W. Michael Gmerek, Jr.

发明人： Nripendra N. Das ,  Thomas E. Mantkowski ,  Jackie L. King ,  Floyd A. Swigert ,  W. Michael Gmerek, Jr.

IPC分类号： C23C1600

摘要： A process for forming a diffusion aluminide coating on an article, such as a component for a gas turbine engine. The process is a vapor phase process that generally entails placing the article in a coating chamber containing an aluminum donor material, without any halide carrier or inert filler present. The aluminum donor material consists essentially of about 20 to about 70 weight percent aluminum, with the balance being chromium or cobalt. While the article is held out of contact with the donor material, coating is initiated in an inert or reducing atmosphere by heating the article and the donor material to vaporize the aluminum constituent of the donor material, which then condenses on the surface of the article and diffuses into the surface to form a diffusion aluminide coating on the article.

摘要翻译： 用于在诸如燃气涡轮发动机的部件的物品上形成扩散铝化物涂层的方法。 该方法是气相法，其通常需要将物品置于包含铝供体材料的涂层室中，而不存在任何卤化物载体或惰性填料。 铝供体材料基本上由约20至约70重量％的铝组成，余量为铬或钴。 虽然制品与供体材料不接触，但是通过加热制品和供体材料来在惰性或还原性气氛中引发涂层，以蒸发供体材料的铝组分，然后将其冷凝在制品的表面上， 扩散到表面以在制品上形成扩散的铝化物涂层。

公开(公告)号：US06616969B2

公开(公告)日：2003-09-09

申请号：US09929595

申请日：2001-08-14

申请人： Jeffrey A. Pfaendtner ,  Joseph D. Rigney ,  Nripendra N. Das ,  Ramgopal Darolia

发明人： Jeffrey A. Pfaendtner ,  Joseph D. Rigney ,  Nripendra N. Das ,  Ramgopal Darolia

IPC分类号： C23C1608

CPC分类号： C23C16/042 ,  C23C16/045 ,  Y02T50/67

摘要： A gas turbine airfoil has an external surface and an internal passage therethrough. The internal passage is selectively coated by providing a source of a flowable precursor coating material in contact with the internal passage of the airfoil, and providing a coating prevention structure overlying at least a portion of the external surface. The flowable precursor coating material is flowed from the source of the flowable precursor coating material and through the internal passage of the airfoil. The coating prevention structure prevents contact of the flowable precursor coating material with the external surface of the airfoil.

摘要翻译： 燃气涡轮机翼型件具有外表面和穿过其的内部通道。 通过提供与翼型件的内部通道接触的可流动的前体涂料的源，选择性地涂覆内部通道，并且提供覆盖在外表面的至少一部分上的防涂层结构。 可流动的前体涂层材料从可流动的前体涂层材料的源头流过翼型件的内部通道。 涂层防止结构防止可流动的前体涂层材料与翼型件的外表面的接触。

公开(公告)号：US06488986B2

公开(公告)日：2002-12-03

申请号：US09771897

申请日：2001-01-29

申请人： Nripendra N. Das ,  Terri K. Brown ,  Matthew D. Saylor ,  Brian H. Pilsner ,  Carl H. Snyder

发明人： Nripendra N. Das ,  Terri K. Brown ,  Matthew D. Saylor ,  Brian H. Pilsner ,  Carl H. Snyder

IPC分类号： C23C1606

CPC分类号： C23C10/08 ,  C23C10/60

摘要： A method for imparting an aluminide coating to an alloy gas turbine engine component, heat treating the component, and quenching the component. The component is exposed to a source of aluminum at an elevated temperature in a coating furnace to deposit an aluminum-based oxidation barrier on the component, heated in the coating furnace to a temperature of at least the solution temperature of the alloy, and quenched by flowing a chilled inert gas around the component in the coating furnace to cool the component from the temperature of at least the solution temperature of the alloy to a temperature at which a gamma′ phase of the alloy is set in the alloy in less than about 10 minutes.

摘要翻译： 一种赋予合金燃气轮机发动机部件的铝化物涂层的方法，对该部件进行热处理，并淬火该部件。 该组件在涂覆炉中在升高的温度下暴露于铝源，以在涂层炉中沉积铝基氧化屏障，在涂层炉中加热至至少合金溶液温度，并通过 使冷却的惰性气体围绕涂覆炉中的组件流动，以将组分从至少合金的溶液温度的温度冷却至合金中γ相以小于约10的温度 分钟。

公开(公告)号：US06458473B1

公开(公告)日：2002-10-01

申请号：US08786814

申请日：1997-01-21

申请人： Jeffrey A. Conner ,  Bangalore A. Nagaraj ,  Joseph A. Heaney, III ,  Nripendra N. Das ,  Patricia A. Zomcik ,  David J. Wortman ,  David V. Rigney ,  Jon C. Schaeffer

发明人： Jeffrey A. Conner ,  Bangalore A. Nagaraj ,  Joseph A. Heaney, III ,  Nripendra N. Das ,  Patricia A. Zomcik ,  David J. Wortman ,  David V. Rigney ,  Jon C. Schaeffer

IPC分类号： B21D3900

CPC分类号： C23C28/00 ,  C03C27/046 ,  C22C5/04 ,  C22C30/00 ,  C23C10/52 ,  F05B2230/90 ,  F05C2253/12 ,  Y10T428/12549 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/12667

摘要： A thermal barrier coating system and a method for forming the coating system on a component designed for use in a hostile thermal environment, such as superalloy turbine, combustor and augmentor components of a gas turbine engine. The method is particularly directed to a thermal barrier coating system that includes a thermal insulating ceramic layer and a diffusion aluminide bond coat on which an aluminum oxide scale is grown to protect the underlying surface of the component and to chemically bond the ceramic layer. The bond coat is formed to contain an additive metal of platinum, palladium, rhodium, chromium and/or silicon, and an additive element of yttrium and/or zirconium, with possible additions of hafnium. The bond coat may be formed by codepositing aluminum with the active element, or by depositing the additive metal and active element on the surface of the component, and then aluminizing to form the diffusion aluminide bond coat.

摘要翻译： 一种热障涂层系统和一种在设计用于恶劣热环境的部件上形成涂层系统的方法，例如燃气涡轮发动机的超级合金涡轮机，燃烧器和增压器部件。 该方法特别涉及一种热障涂层系统，其包括绝热陶瓷层和扩散铝化物粘合涂层，其上生长氧化铝垢以保护部件的下表面并化学粘合陶瓷层。 形成粘合涂层以包含铂，钯，铑，铬和/或硅的添加金属和钇和/或锆的添加元素，可能添加铪。 粘结涂层可以通过将铝与活性元素共沉积，或者通过将添加剂金属和活性元素沉积在组分的表面上，然后镀铝以形成扩散铝化物粘合涂层而形成。

公开(公告)号：US06555179B1

公开(公告)日：2003-04-29

申请号：US09527270

申请日：2000-03-17

申请人： Jim D. Reeves ,  Bhupendra K. Gupta ,  Nripendra N. Das

发明人： Jim D. Reeves ,  Bhupendra K. Gupta ,  Nripendra N. Das

IPC分类号： C23C406

CPC分类号： C23C28/3215 ,  C23C4/18 ,  C23C10/02 ,  C23C10/08 ,  C23C28/321 ,  C23C28/325 ,  C23C28/3455

摘要： A thermal barrier coating system and a method for forming the coating system on an article designed for use in a hostile thermal environment. The method is particularly directed to a coating system that includes a plasma-sprayed MCrAlY bond coat on which a thermal-insulating APS ceramic layer is deposited, in which the oxidation resistance of the bond coat and the spallation resistance of the ceramic layer are substantially increased by vapor phase aluminizing the bond coat. The bond coat is deposited to have a surface area ratio of at least 1.4 and a surface roughness of at least 300 &mgr;inch Ra in order to promote the adhesion of the ceramic layer. The bond coat is then overcoat aluminized using a vapor phase process that does not alter the surface area ratio of the bond coat. This process is carried out at relatively low temperatures that promote inward diffusion of aluminum relative to outward diffusion of the bond coat constituents, particularly nickel and other refractory elements. The process conditions also provide sufficient vapor phase activity at the surface of the bond coat that promote aluminum atomic movement through the bond coat.

摘要翻译： 一种热障涂层系统和一种在设计用于恶劣热环境中的物品上形成涂层系统的方法。 该方法特别涉及包括等离子体喷涂的MCrAlY粘结涂层的涂覆体系，其上沉积有绝热的APS陶瓷层，其中粘合涂层的抗氧化性和陶瓷层的抗剥落性大大增加 通过气相渗透粘结涂层。 为了促进陶瓷层的粘附，沉积粘合涂层以使表面积比至少为1.4，表面粗糙度为至少300μm。 然后使用不改变粘结涂层的表面积比的气相方法将粘合涂层进行外涂镀铝。 该过程在相对低的温度下进行，其促进铝相对于粘合涂层成分，特别是镍和其它难熔元素的向外扩散的向内扩散。 工艺条件还在粘合涂层的表面提供足够的气相活性，促进铝原子通过粘结涂层的运动。

公开(公告)号：US06332926B1

公开(公告)日：2001-12-25

申请号：US09373433

申请日：1999-08-11

申请人： Jeffrey A. Pfaendtner ,  Joseph D. Rigney ,  Nripendra N. Das ,  Ramgopal Darolia

发明人： Jeffrey A. Pfaendtner ,  Joseph D. Rigney ,  Nripendra N. Das ,  Ramgopal Darolia

IPC分类号： C23C1600

CPC分类号： C23C16/042 ,  C23C16/045 ,  Y02T50/67

摘要： A gas turbine airfoil has an external surface and an internal passage therethrough. The internal passage is selectively coated by providing a source of a flowable precursor coating material in contact with the internal passage of the airfoil, and providing a coating prevention structure overlying at least a portion of the external surface. The flowable precursor coating material is flowed from the source of the flowable precursor coating material and through the internal passage of the airfoil. The coating prevention structure prevents contact of the flowable precursor coating material with the external surface of the airfoil.

摘要翻译： 燃气涡轮机翼型件具有外表面和穿过其的内部通道。 通过提供与翼型件的内部通道接触的可流动的前体涂料的源，选择性地涂覆内部通道，并且提供覆盖在外表面的至少一部分上的防涂层结构。 可流动的前体涂层材料从可流动的前体涂层材料的源头流过翼型件的内部通道。 涂层防止结构防止可流动的前体涂层材料与翼型件的外表面的接触。

公开(公告)号：US6014263A

公开(公告)日：2000-01-11

申请号：US71109

申请日：1998-05-04

申请人： Jon C. Schaeffer ,  Nripendra N. Das ,  Brian F. Mickle ,  Ching-Ho Wang ,  Matthew S. Tomaszewski ,  Kevin G. McAllister

发明人： Jon C. Schaeffer ,  Nripendra N. Das ,  Brian F. Mickle ,  Ching-Ho Wang ,  Matthew S. Tomaszewski ,  Kevin G. McAllister

IPC分类号： G02B1/10 ,  G02B27/00 ,  G02B3/00

CPC分类号： G02B27/0006 ,  G02B1/105

摘要： A method for preventing clouding of a lens employed in a high-temperature oxidizing environment, an example of which is a lens of a pyrometer used to sense exhaust gas temperature (EGT) of a gas turbine engine. Clouding is prevented by inhibiting the generation of volatile oxide species that react with high-temperature lens materials, forming deposits including oxides of chromium, molybdenum and other elements having volatile oxide species. The method is particularly directed to a pyrometer whose lens is formed of sapphire (alumina) or silica, and is mounted within a structure formed of a material containing chromium and/or molybdenum, such as a superalloy or stainless steel. The method entails forming an alumina scale-forming barrier coating such as a diffusion aluminide on surfaces of the structure that are subject to oxidation and high temperatures. According to the invention, the alumina scale formed by the barrier coating inhibits the generation of other oxides at the coated surfaces, which would otherwise form volatile oxides that react with and form deposit on the lens. By inhibiting the formation of oxides other than alumina on surfaces surrounding the lens, lens clouding caused from volatile oxides is avoided. As a result, the optical performance of the lens is not degraded, and the precision of a pyrometer employing the lens to sense temperatures is maintained during operation of the engine.

摘要翻译： 一种用于防止在高温氧化环境中使用的透镜的混浊的方法，其实例是用于感测燃气涡轮发动机的排气温度（EGT）的高温计的透镜。 通过抑制与高温透镜材料反应的挥发性氧化物物质的产生，形成含有铬，钼和其它具有挥发性氧化物的元素的沉积物来防止云层。 该方法特别涉及其透镜由蓝宝石（氧化铝）或二氧化硅形成的高温计，并且安装在由含有铬和/或钼的材料（例如超级合金或不锈钢）形成的结构内。 该方法需要在经受氧化和高温的结构的表面上形成氧化铝垢形成阻挡涂层，例如扩散铝化物。 根据本发明，通过阻挡涂层形成的氧化铝垢阻止了在涂覆表面产生其它氧化物，否则其将形成与透镜反应并形成沉积在透镜上的挥发性氧化物。 通过抑制在透镜周围的表面上形成氧化铝以外的氧化物，避免了由挥发性氧化物引起的透镜混浊。 结果，透镜的光学性能不降低，并且在发动机的操作期间保持采用透镜感测温度的高温计的精度。