Abstract: A stator vane assembly is provided, particularly for the first row of stationary vanes of a gas turbine, utilizing ceramic vanes. Each individual vane assembly consists of an airfoil vane with a separate end cap at each end for supporting the vane in position. In accordance with the invention, the engaging surfaces of the vane and of each adjacent end cap are curved surfaces of compound curvature forming engaging pivot and seat surfaces, the major and minor radii of the pivot surface being less than the corresponding major and minor radii of the seat surface, and the curvature of the pivot surface being such that thermal ratcheting of the vane with respect to the end caps is prevented.

Abstract: A ceramic member for a gas turbine is produced by a method including, forming the member to the desired configuration by conventional means and then finishing it to the desired size by a surface finish and subsequently burnishing the surface to a highly polished finish of the order of 3 to 6 RMS, and rounding off the sharp edges to a small radius in the range of 0.010 to 0.020 inch. These finishing operations are performed in the direction in which the maximum stress is to be applied to the member in its use in the turbine.

Abstract: Cushions made of metal wire provide passageways for cooling air and a resilient layer between metal and ceramic parts in a ceramic blade assembly for a gas turbine.