Engine hot section component and method for making the same

Abstract

One embodiment of the present invention is a unique engine hot section component having a coating system operative to reduce heat transfer to the hot section component. Another embodiment is a unique method for making a gas turbine engine hot section component with a coating system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines, hot section components and coating systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

What is claimed is: 
     
         1 . An engine hot section component, comprising:
 a substrate having a surface in line-of-sight radiative communication with a combustion flame during operation of an engine; and   a plurality of pairs of alternating layers of a first radiation barrier coating composition and a second radiation barrier coating composition on the substrate between the substrate and the combustion flame,   wherein:
 the first radiation barrier coating composition comprises tantalum oxide and has a first refraction index, 
 the second radiation barrier coating composition comprises mullite and has a second refraction index different from the first refraction index. 
   
     
     
         2 . The engine hot section component of  claim 1 , wherein the first radiation barrier coating composition and the second radiation barrier coating composition are configured to refract and reflect radiant energy at preselected wavelengths of radiation from the combustion flame away from the substrate. 
     
     
         3 . The engine hot section component of  claim 2 , wherein the preselected wavelengths of radiation range from about 200 nm to about 700 nm. 
     
     
         4 . The engine hot section component of  claim 1 , wherein a first layer of the first radiation barrier coating composition is between the substrate and the combustion flame and a second layer of the second radiation barrier composition is between the first layer of the first radiation barrier coating composition and the combustion flame. 
     
     
         5 . The engine hot section component of  claim 1 , wherein a first layer of the second radiation barrier coating composition is between the substrate and the combustion flame and a second layer of the first radiation barrier coating composition is positioned between the first layer of the second radiation barrier coating composition and the combustion flame. 
     
     
         6 . An engine hot section component, comprising:
 a substrate having a surface in line-of-sight radiative communication with a combustion flame during operation of an engine;   a thermal barrier coating (TBC) on the substrate between the substrate and the combustion flame, wherein a surface of the TBC is finished to enhance reflective properties of the TBC; and   a plurality of pairs of alternating layers of a first radiation barrier coating composition and a second radiation barrier coating composition on the TBC,   wherein:
 the first radiation barrier coating composition comprises tantalum oxide and has a first refraction index, and 
 the second radiation barrier coating composition comprises mullite and has a second refraction index different from the first refraction index. 
   
     
     
         7 . The engine hot section component of  claim 6 , wherein the first radiation barrier coating composition and the second radiation barrier coating composition are configured to refract and reflect radiant energy at preselected wavelengths of radiation from the combustion flame away from the substrate. 
     
     
         8 . The engine hot section component of  claim 7 , wherein the preselected wavelengths of radiation range from about 200 nm to about 700 nm. 
     
     
         9 . The engine hot section component of any  claim 6 , wherein a first layer of the first radiation barrier coating composition is between the substrate and the combustion flame and a second layer of the second radiation barrier composition is between the first layer of the first radiation barrier coating and the combustion flame. 
     
     
         10 . The engine hot section component of  claim 6 , wherein a first layer of the second radiation barrier coating composition is between the substrate and the combustion flame and a second layer of the first radiation barrier coating composition is between the first layer of the second radiation barrier coating composition and the combustion flame. 
     
     
         11 . The engine hot section component of  claim 6 , wherein the TBC comprises Yttria-Stabilized Zirconia (YSZ). 
     
     
         12 . The engine hot section component of  claim 11 , wherein the TBC comprises an 8% YSZ layer. 
     
     
         13 . The engine hot section component of  claim 6 , further comprising a bond coat between the substrate and the TBC. 
     
     
         14 . The engine hot section component of  claim 13 , wherein the bond coat comprises an MCrAlY alloy, and where M=Co, Ni or Co/Ni. 
     
     
         15 . The engine hot section component of  claim 6 , further comprising an adhesion aid between the TBC and the plurality of pairs of alternating layers. 
     
     
         16 . The engine hot section component of  claim 6 , further comprising an adhesion aid between two adjacent layers of the plurality of pairs of alternating layers. 
     
     
         17 . The engine hot section component of  claim 16 , wherein the adhesion aid includes at least one of alumina, mullite, a silicate, or zircon. 
     
     
         18 . The engine hot section component of  claim 16 , wherein a surface of the adhesion aid is finished to enhance reflective properties of the adhesion aid. 
     
     
         19 . The engine hot section component of  claim 6 , wherein a surface of at least one layer of the plurality of pairs of alternating layers is finished to enhance reflective properties of the at least one layer of the plurality of pairs of alternating layers.