Methods of protecting metallic components against corrosion using chromium-containing thin films

Abstract

Protected aerospace components are provided and contain a nanolaminate film stack disposed on a surface of an aerospace component, where the nanolaminate film stack comprises alternating layers of a chromium-containing layer and a second deposited layer. The chromium-containing layer can include metallic chromium, chromium oxide, chromium nitride, chromium carbide, chromium silicide, or any combination thereof.

What is claimed is: 
     
         1 . A protected aerospace component, comprising:
 a nanolaminate film stack disposed on a surface of an aerospace component, wherein the nanolaminate film stack comprises alternating layers of a chromium-containing layer and a second deposited layer.   
     
     
         2 . The protected aerospace component of  claim 1 , wherein the aerospace component is a turbine blade, a turbine vane, a support member, a frame, a rib, a fin, a pin fin, a combustor fuel nozzle, a combustor shield, an internal cooling channel, or any combination thereof. 
     
     
         3 . The protected aerospace component of  claim 1 , wherein the surface of the aerospace component is an interior surface of the aerospace component. 
     
     
         4 . The protected aerospace component of  claim 3 , wherein the interior surface is within a cavity of the aerospace component, and the cavity has an aspect ratio of about 5 to about 1,000. 
     
     
         5 . The protected aerospace component of  claim 1 , wherein the surface of the aerospace component comprises nickel, nickel superalloy, aluminum, chromium, iron, titanium, hafnium, alloys thereof, or any combination thereof. 
     
     
         6 . The protected aerospace component of  claim 1 , wherein the second deposited layer comprises aluminum oxide, aluminum nitride, silicon oxide, silicon nitride, silicon carbide, yttrium oxide, yttrium nitride, yttrium silicon nitride, hafnium oxide, hafnium nitride, hafnium silicide, hafnium silicate, titanium oxide, titanium nitride, titanium silicide, titanium silicate, or any combination thereof. 
     
     
         7 . The protected aerospace component of  claim 6 , wherein the second deposited layer comprises aluminum oxide and at least one of aluminum nitride, yttrium oxide, yttrium nitride, yttrium silicon nitride, hafnium oxide, hafnium nitride, hafnium silicide, hafnium silicate, titanium oxide, titanium nitride, titanium silicide, titanium silicate, or any combination thereof. 
     
     
         8 . The protected aerospace component of  claim 1 , wherein the chromium-containing layer contains metallic chromium, chromium oxide, chromium nitride, chromium carbide, chromium silicide, or any combination thereof. 
     
     
         9 . The protected aerospace component of  claim 1 , wherein the chromium-containing layer was formed by a chemical vapor deposition process. 
     
     
         10 . The protected aerospace component of  claim 1 , wherein the chromium-containing layer was formed by an atomic layer deposition process. 
     
     
         11 . The protected aerospace component of  claim 1 , wherein the chromium- containing layer was formed from a chromium precursor during by a vapor deposition process, wherein the chromium precursor comprises bis(cyclopentadiene) chromium, bis(pentamethylcyclopentadiene) chromium, bis(isopropylcyclopentadiene) chromium, bis(ethylbenzene) chromium, chromium hexacarbonyl, chromium acetylacetonate, chromium hexafluoroacetylacetonate, a chromium diazadienyl, isomers thereof, complexes thereof, abducts thereof, salts thereof, or any combination thereof. 
     
     
         12 . The protected aerospace component of  claim 11 , wherein the chromium diazadienyl has a chemical formula of: 
       
         
           
           
               
               
           
         
         wherein each R and R′ is independently selected from H, C1-C6 alkyl, aryl, acyl, alkylamido, hydrazido, silyl, aldehyde, keto, C2-C4 alkenyl, alkynyl, or substitutes thereof. 
       
     
     
         13 . A protected aerospace component, comprising:
 a nanolaminate film stack disposed on a surface of an aerospace component, wherein:
 the nanolaminate film stack comprises alternating layers of a chromium-containing layer and a second deposited layer; and 
 the aerospace component is a turbine blade, a turbine vane, a combustor fuel nozzle, an internal cooling channel, or any combination thereof. 
   
     
     
         14 . The protected aerospace component of  claim 13 , wherein the surface of the aerospace component is an interior surface of the aerospace component, and wherein the interior surface is within a cavity of the aerospace component, and the cavity has an aspect ratio of about 5 to about 1,000. 
     
     
         15 . The protected aerospace component of  claim 13 , wherein the chromium-containing layer contains metallic chromium, chromium oxide, chromium nitride, chromium carbide, chromium silicide, or any combination thereof. 
     
     
         16 . The protected aerospace component of  claim 13 , wherein the surface of the aerospace component comprises nickel, nickel superalloy, aluminum, chromium, iron, titanium, hafnium, alloys thereof, or any combination thereof. 
     
     
         17 . The protected aerospace component of  claim 13 , wherein the second deposited layer comprises aluminum oxide, aluminum nitride, silicon oxide, silicon nitride, silicon carbide, yttrium oxide, yttrium nitride, yttrium silicon nitride, hafnium oxide, hafnium nitride, hafnium silicide, hafnium silicate, titanium oxide, titanium nitride, titanium silicide, titanium silicate, or any combination thereof. 
     
     
         18 . A protected aerospace component, comprising:
 a nanolaminate film stack disposed on a surface of an aerospace component, wherein:
 the nanolaminate film stack comprises alternating layers of a chromium-containing layer and a second deposited layer; 
 the surface of the aerospace component comprises nickel, nickel superalloy, aluminum, chromium, iron, titanium, hafnium, alloys thereof, or any combination thereof; and 
 the second deposited layer comprises aluminum oxide, aluminum nitride, silicon oxide, silicon nitride, silicon carbide, yttrium oxide, yttrium nitride, yttrium silicon nitride, hafnium oxide, hafnium nitride, hafnium silicide, hafnium silicate, titanium oxide, titanium nitride, titanium silicide, titanium silicate, or any combination thereof. 
   
     
     
         19 . The protected aerospace component of  claim 18 , wherein the aerospace component is a turbine blade, a turbine vane, a support member, a frame, a rib, a fin, a pin fin, a combustor fuel nozzle, a combustor shield, an internal cooling channel, or any combination thereof. 
     
     
         20 . The protected aerospace component of  claim 18 , wherein:
 the surface of the aerospace component is an interior surface of the aerospace component;   the interior surface is within a cavity of the aerospace component; and   the cavity has an aspect ratio of about 10 to about 1,000.