Coatings, method of manufacture, and the articles derived therefrom

Abstract

A turbine component comprises a substrate; and a crystalline coating disposed on a surface of the substrate, wherein the crystalline coating comprises tin and yttrium in an amount greater than or equal to about 0.05 atomic percent based upon the total coating. A method of making a turbine component comprises disposing a coating composition on a substrate, wherein the coating composition comprises tin and yttrium in an amount greater than or equal to about 0.1 atomic percent based upon the total coating composition. A crystalline coating comprises tin and yttrium in an amount greater than or equal to about 0.05 atomic percent based upon the total coating.

1 . A turbine component comprising: 
 a substrate; and    a crystalline coating disposed on a surface of the substrate, wherein the crystalline coating comprises tin and yttrium in an amount greater than or equal to about 0.05 atomic percent based upon the total coating.    
     
     
         2 . The turbine component of  claim 1 , wherein the substrate is a niobium based refractory metal intermetallic composite comprising titanium, hafnium, silicon, chromium, and niobium or a molybdenum-silicide based composite comprising molybdenum, silicon, and either boron, chromium or a combination of boron and chromium.  
     
     
         3 . The turbine component of  claim 1 , wherein the substrate is selected from the group consisting of rotating blades, non-rotating vanes, shrouds, nozzles, and combustors.  
     
     
         4 . The turbine component of  claim 1 , wherein the substrate is part of aircraft turbine system, a landcraft turbine system or a watercraft turbine system.  
     
     
         5 . The turbine component of  claim 1 , wherein the substrate further comprises a thermal barrier coating disposed on a surface of the crystalline coating on a side opposite the substrate.  
     
     
         6 . The turbine component of  claim 1 , wherein the crystalline coating further comprises chromium and aluminum.  
     
     
         7 . The turbine component of  claim 1 , wherein the crystalline coating further comprises about 25 to about 60 atomic percent chromium, up to about 20 atomic percent aluminum, about 2 to about 40 atomic percent niobium, about 5 to about 67 atomic percent silicon, about 2 to about 40 atomic percent titanium, up to about 20 atomic percent germanium, and up to about 10 atomic percent iron, based upon the total coating.  
     
     
         8 . A turbine system comprising the turbine component of  claim 1 .  
     
     
         9 . A method of making a turbine component comprising: 
 disposing a coating composition on a substrate, wherein the coating composition comprises tin and yttrium in an amount greater than or equal to about 0.1 atomic percent based upon the total coating composition.    
     
     
         10 . The method of  claim 9 , wherein the disposing comprises: 
 applying to the substrate by dipping, painting, spray painting, or combinations comprising at least one of the foregoing, a slurry comprising tin and yttrium in an amount effective to provide a coating comprising tin and yttrium in an amount of greater than or equal to about 0.05 atomic percent based upon the total coating; and    heat treating the substrate for at least about one hour at a temperature of at least about 1200° C.    
     
     
         11 . The method of  claim 9 , wherein the substrate is a niobium based refractory metal intermetallic composite comprising titanium, hafnium, silicon, chromium, and niobium or a molybdenum-silicide based composite comprising molybdenum, silicon, and either boron or chromium.  
     
     
         12 . The method of  claim 9 , wherein the crystalline coating further comprises chromium and aluminum.  
     
     
         13 . The method of  claim 9 , wherein the crystalline coating further comprises about 25 to about 60 atomic percent chromium, up to about 20 atomic percent aluminum, about 2 to about 40 atomic percent niobium, about 5 to about 67 atomic percent silicon, about 2 to about 40 atomic percent titanium, up to about 20 atomic percent germanium, and up to about 10 atomic percent iron, based upon the total coating.  
     
     
         14 . The method of  claim 9 , wherein the crystalline coating has a thickness of about 10 microns to about 200 microns.  
     
     
         15 . The method of  claim 9 , wherein a thermal barrier coating is further disposed on a surface of the crystalline coating on a side opposite the substrate.  
     
     
         16 . A turbine system comprising the turbine component manufactured by the method of  claim 9 .  
     
     
         17 . A crystalline coating comprising tin and yttrium in an amount greater than or equal to about 0.05 atomic percent based upon the total coating.  
     
     
         18 . The crystalline coating of  claim 17 , further comprising chromium and aluminum.  
     
     
         19 . The crystalline coating of  claim 17 , further comprising about 10 to about 67 atomic percent chromium, about 5 to about 55 atomic percent aluminum, and about 15 to about 45 atomic percent of a combination of niobium and titanium, based upon the total coating.  
     
     
         20 . The crystalline coating of  claim 17 , further comprising up to about 15 atomic percent silicon, 15 to about 52 atomic percent chromium, about 30 to about 50 atomic percent aluminum, about 10 to about 25 atomic percent niobium, about 5 to about 20 atomic percent titanium, up to about 15 atomic percent germanium, and up to about 8 atomic percent iron, based upon the total coating.  
     
     
         21 . The crystalline coating of  claim 17 , further comprising about 20 atomic percent chromium, about 37.9 atomic percent aluminum, about 10 atomic percent niobium, about 8 atomic percent titanium, about 10 atomic percent silicon, about 8 atomic percent germanium, and about 4 atomic percent iron, based upon the total coating.  
     
     
         22 . The crystalline coating of  claim 17 , comprising about 4 atomic percent tin, and about 0.2 atomic percent yttrium and further comprises about 20 atomic percent chromium, about 45 atomic percent aluminum, about 14.8 atomic percent niobium, about 12 atomic percent titanium, about 4 atomic percent iron, based upon the total coating.  
     
     
         23 . The crystalline coating of  claim 17 , comprising about 25 to about 60 atomic percent chromium, up to about 20 atomic percent aluminum, about 2 to about 40 atomic percent niobium, about 5 to about 67 atomic percent silicon, about 2 to about 40 atomic percent titanium, up to about 20 atomic percent germanium, and up to about 10 atomic percent iron, based upon the total coating.  
     
     
         24 . The crystalline coating of  claim 17 , comprising about 40 to about 60 atomic percent chromium, up to about 20 atomic percent aluminum, about 20 to about 25 atomic percent niobium, about 10 to about 20 atomic percent silicon, about 8 to about 10 atomic percent titanium, and up to about 10 atomic percent iron, based upon the total coating.  
     
     
         25 . The crystalline coating of  claim 17 , comprising about 25 to about 40 atomic percent chromium, up to about 4 atomic percent aluminum, about 5 to about 15 atomic percent niobium, about 49 to about 64 atomic percent silicon, about 5 to about 10 atomic percent titanium, and up to about 4 atomic percent iron, based upon the total coating.  
     
     
         26 . The crystalline coating of  claim 17 , wherein the coating has C14 Laves of the form (Nb,Ti)(Cr,Si,Al) 2 , with about 30 to about 37 atomic percent of niobium or combinations comprising niobium and titanium, and about 63 to about 70 atomic percent of chromium, silicon and aluminum.  
     
     
         27 . The crystalline coating of  claim 17 , wherein the coating comprises primary phases of the form (Nb,Ti,Cr)Al 3 , (Nb,Ti,Cr) 2 Al, Nb 5 Si 3 , Ti 5 Si 3 , (Cr,Nb,Ti) 5 Si 3 , (Cr, Nb, Ti) 11 Si 8 , (Cr,Ti,Nb) 6 Si 5 , CrSi 2 , CrSi, Cr 3 Si or combinations comprising at least one of the foregoing phases.