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Browse by: INVENTOR PATENT HOLDER PATENT NUMBER DATE
 
 
Inventor:
Goedjen; John G.
Address:
Oviedo, FL
No. of patents:
7
Patents:












Patent Number Title Of Patent Date Issued
6365281 Thermal barrier coatings for turbine components April 2, 2002
A turbine component, such as a turbine blade having a metal substrate (22) is coated with a metal MCrAlY alloy layer (24) and then a thermal barrier layer (20) selected from LaAlO.sub.3, NdAlO.sub.3, La.sub.2 Hf.sub.2 O.sub.7, Dy.sub.3 Al.sub.5 O.sub.12, HO.sub.3 Al.sub.3 O.sub.12, E
6306515 Thermal barrier and overlay coating systems comprising composite metal/metal oxide bond coating October 23, 2001
The present invention generally describes multilayer coating systems comprising a composite metal/metal oxide bond coat layer. The coating systems may be used in gas turbines.
6231998 Thermal barrier coating May 15, 2001
A thermal barrier coating for hot gas path components of a combustion turbine based on a zirconia-scandia system. A layer of zirconium scandate having the hexagonal Zr.sub.3 Sc.sub.4 O.sub.12 structure is formed directly on a superalloy substrate or on a bond coat formed on the subst
6207297 Barrier layer for a MCrAlY basecoat superalloy combination March 27, 2001
A turbine component contains a substrate (22) such as a superalloy, a basecoat (24) of the type MCrAlY, and a continuous barrier layer (28) between the substrate and basecoat, where the barrier layer (28) is made of an alloy of (Re, Ta, Ru, Os)X, where X can be Ni, Co or their mixture,
6129988 Gaseous modification of MCrAlY coatings October 10, 2000
The present invention generally describes methods for modifying MCrAlY coatings by using gaseous carburization, gaseous nitriding or gaseous carbonitriding. The modified MCrAlY coatings are useful in thermal barrier coating systems, which may be used in gas turbine engines.
6106959 Multilayer thermal barrier coating systems August 22, 2000
The present invention generally describes multilayer thermal barrier coating systems and methods of making the multilayer thermal barrier coating systems. The thermal barrier coating systems comprise a first ceramic layer, a second ceramic layer, a thermally grown oxide layer, a meta
6060174 Bond coats for turbine components and method of applying the same May 9, 2000
A substrate (12) such as a superalloy turbine component is coated with a basecoat (14) of the type MCrAlY which also contains boron, where the amount of boron in the basecoat is in a concentration gradient where more boron is present near the top (16) than the bottom (20) of the basecoat










 
 
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