公开(公告)号：US06607789B1

公开(公告)日：2003-08-19

申请号：US09842503

申请日：2001-04-26

申请人： Joseph David Rigney ,  Michael James Weimer ,  Bangalore Aswatha Nagaraj ,  Yuk-Chiu Lau

发明人： Joseph David Rigney ,  Michael James Weimer ,  Bangalore Aswatha Nagaraj ,  Yuk-Chiu Lau

IPC分类号： C23C404

CPC分类号： C23C28/3455 ,  C23C4/02 ,  C23C28/321 ,  C23C28/345 ,  Y10T428/12611 ,  Y10T428/12944

摘要： A method for forming a thermal barrier coating system on an article subjected to a hostile thermal environment, such as the hot gas path components of a gas turbine engine. The coating system is generally comprised of a ceramic layer and an environmentally resistant beta phase nickel aluminum intermetallic (&bgr;-NiAl) bond coat that adheres the ceramic layer to the component surface. A thin aluminum oxide scale forms on the surface of the &bgr;-NiAl during heat treatment. The &bgr;-NiAl may contain alloying elements in addition to nickel and aluminum in order to increase the environmental resistance of the &bgr;-NiAl. The &bgr;-NiAl powder having a size in the range of 20-50 microns is applied using air plasma spray techniques to produce a surface having a roughness of 400 microinches or rougher. The ceramic top coat can be applied using inexpensive thermal spray techniques to greater thicknesses than achievable otherwise because of the rough surface finish of the underlying &bgr;-NiAl bond coat.

摘要翻译： 一种用于在遭受恶劣热环境的制品（例如燃气涡轮发动机的热气路径部件）上形成热障涂层系统的方法。 涂层系统通常包括陶瓷层和环境友好的β相镍铝金属间化合物（β-NiAl）粘合涂层，其将陶瓷层粘附到组件表面。 在热处理期间，在β-NiAl的表面上形成薄的氧化铝垢。 除了镍和铝之外，β-NiAl还可以含有合金元素，以增加β-NiAl的耐环境性。 使用空气等离子喷涂技术施加尺寸在20-50微米范围内的β-NiAl粉末，以产生粗糙度为400微英寸或更粗糙的表面。 陶瓷面漆可以使用廉价的热喷涂技术应用于厚度大于其它可能的厚度，因为底层β-NiAl粘合涂层的粗糙表面光洁度。

公开(公告)号：US06502304B2

公开(公告)日：2003-01-07

申请号：US09855444

申请日：2001-05-15

申请人： Joseph David Rigney ,  William Scott Walston ,  Richard John Grylls

发明人： Joseph David Rigney ,  William Scott Walston ,  Richard John Grylls

IPC分类号： B23P1500

CPC分类号： C23C4/00 ,  F01D5/20 ,  F01D5/288 ,  F01D11/14 ,  Y02T50/67 ,  Y10T29/49318 ,  Y10T29/49321 ,  Y10T29/49323 ,  Y10T29/49336

摘要： Optimized tip performance for turbine airfoils is obtained through a sequenced manufacturing process. The turbine airfoils are assembled into the dovetail slots of a turbine disk. The tips of the turbine airfoils assembled in the turbine disk are then measured to determine the turbine airfoils that do not have adequate tip clearance. The tips of those turbine airfoils that do not have adequate tip clearance are then machined to obtain adequate tip clearance. Once all the turbine airfoils have adequate tip clearance, environmental coatings and/or thermal barrier coatings are applied to the blade tips.

摘要翻译： 通过有序的制造过程可以获得涡轮机翼型的优化喷嘴性能。 涡轮机翼片组装到涡轮盘的燕尾槽中。 然后测量组装在涡轮盘中的涡轮翼型件的尖端，以确定不具有足够顶端间隙的涡轮机翼型。 然后对那些没有足够的顶端间隙的涡轮机翼型的末端进行机加工以获得足够的顶端间隙。 一旦所有的涡轮机翼片具有足够的顶端间隙，则将环境涂层和/或热障涂层施加到叶片尖端。