Method of making a turbine engine component

A method of making a turbine engine component having a shroud ring with a plurality of airfoils disposed in an annular array, said method comprising the steps of providing a plurality of airfoils formed of a material having a first melting temperature, forming on at least one end portion of each of the airfoils a heat resistant layer which extends at least partially around the one end portion of each of the airfoils and has a second melting temperature which is greater than the first melting temperature, positioning the plurality of airfoils in an annular array, forming a mold having a shroud ring mold cavity in which the heat resistant layer on the one end portion of each of the airfoils is at least partially disposed, filling the shroud ring mold cavity with molten metal, engaging the heat resistant layer on the one end portion of each of the airfoils with the molten metal during performance of said step of filling the shroud ring mold cavity with molten metal, and solidifying the molten metal in the shroud ring mold cavity to form the shroud ring, said step of solidifying molten metal in the shroud ring mold cavity includes leaving joints between the one end portion of each of the airfoils and the solidified metal in the shroud ring mold cavity free of bonds to enable thermal expansion to occur between the airfoils and the shroud ring during use of the turbine engine component, wherein said step of forming a heat resistant layer includes forming a layer of chromium sesquioxide (Cr.sub.2 O.sub.3) which extends at least partially around the one end portion of each of the airfoils .