Ceramic matrix composite components with inserts

Abstract

A gas turbine engine is disclosed that includes a compressor, a combustor, and a turbine. The turbine includes a turbine shroud having a blade track formed from a ceramic matrix composite material. The combustor includes a combustor liner formed from one or more ceramic matrix composite tiles.

What is claimed is: 
     
         1 . A turbine shroud adapted for use in a gas turbine engine, the turbine shroud comprising
 a blade track made from ceramic matrix composite materials and formed to include an aperture extending through at least a portion of the blade track, and   an insert formed to include a passageway that extends through the aperture to conduct gasses through the aperture while blocking gasses from interacting with surfaces of the blade track that define the aperture.   
     
     
         2 . The assembly of  claim 1 , wherein the insert includes a liner that forms the passageway and a retention flange that extends outwardly from the liner along a side of the blade track that extends away from the aperture to block movement of the liner through the aperture away from the side of the blade track. 
     
     
         3 . The assembly of  claim 2 , wherein the aperture formed in the blade track is a round bore that extends along an axis and the passageway formed in the insert is coaxial with the aperture. 
     
     
         4 . The assembly of  claim 3 , wherein the liner has an outer diameter that is greater than a diameter of the aperture so that the insert is interference fit with the blade track. 
     
     
         5 . The assembly of  claim 3 , further comprising a bond layer between the liner and a side wall that defines the aperture to couple the insert to the blade track. 
     
     
         6 . The assembly of  claim 5 , wherein the bond layer is made of silicon-containing braze material. 
     
     
         7 . The assembly of  claim 5 , wherein the bond layer is made of a silicon-containing cement material. 
     
     
         8 . The assembly of  claim 2 , wherein the insert is a monolithic component made from a substantially homogenous material. 
     
     
         9 . The assembly of  claim 8 , wherein the material is silicon carbide. 
     
     
         10 . The assembly of  claim 8 , wherein the material is one of the following: aluminum oxide, zirconium oxide, or rare earth oxide. 
     
     
         11 . The assembly of  claim 8 , wherein the material is a rare earth silicate. 
     
     
         12 . The assembly of  claim 8 , wherein the material is one of the following: a rare earth aluminate, an alkaline aluminosilicate, or mullite. 
     
     
         13 . A combustor adapted for use in a gas turbine engine, the combustor comprising
 a shell made from metallic materials,   a liner tile made from ceramic matrix composite materials that is coupled to the shell and is formed to include an aperture extending through at least a portion of the liner tile, and   an insert formed to include a passageway that extends through the aperture to shield surfaces of the liner tile that define the aperture.   
     
     
         14 . The combustor of  claim 13 , further comprising a fastener that extends through the passageway to couple the liner tile to the shell. 
     
     
         15 . The combustor of  claim 13 , wherein the insert includes a liner that forms the passageway and a retention flange that extends outwardly from the liner along a side of the liner tile that extends away from the aperture to block the liner from moving through the aperture away from the side. 
     
     
         16 . The assembly of  claim 15 , wherein the aperture formed in the liner tile is a round bore that extends along an axis and the passageway formed in the insert is coaxial with the aperture. 
     
     
         17 . An assembly adapted for use in a gas turbine engine, the assembly comprising
 a component made from ceramic matrix composite materials and formed to include an aperture extending through the component from a relatively-high pressure side of the component to a relatively-low pressure side of the component, and   an insert formed to include a passageway that extends through the aperture to conduct gasses through the aperture from the relatively-high pressure side of the component to the relatively-low pressure side of the component while blocking gasses from interacting with surfaces of the component that define the aperture.   
     
     
         18 . The assembly of  claim 17 , wherein the insert includes a liner that forms the passageway and a retention flange that extends outwardly from the liner along the relatively-high pressure side of the component to block the liner from moving through the aperture toward the relatively-low pressure side of the component. 
     
     
         19 . The assembly of  claim 18 , wherein the aperture formed in the component is a round bore that extends along an axis and the passageway formed in the insert is coaxial with the aperture. 
     
     
         20 . The assembly of  claim 19 , further comprising a fastener that extends through the passageway to couple the component to another part of the assembly.