Abstract: A turbine vane array (10) for a combustion assembly (8) in a combustion turbine engine. The vane array (10) includes a plurality of stationary vane assemblies (12), each vane assembly (12) including at least one airfoil (24) and inner and outer shroud segments (26, 28) attached to opposing ends of the airfoil (24). The inner and outer shroud segments (26, 28) each include an inner face (34, 36) facing toward a gas path (13) extending through the vane array (10). A removable cover structure may be provided on the inner faces (34, 36) of the inner and outer shroud segments (26, 28). The cover structure may include removably attached insert elements (72, 72?) that are positioned on the inner faces (34, 36) extending between upstream edges (44) and downstream edges (46) of the shroud segments (26, 28) and extending between adjacent airfoils (24).

Abstract: A turbine vane assembly includes a turbine vane having first and second shrouds with an elongated airfoil extending between. Each end of the airfoil transitions into a shroud at a respective junction. Each of the shrouds has a plurality of cooling passages, and the airfoil has a plurality of cooling passages extending between the first and second shrouds. A substantially flat inner plate and an outer plate are coupled to each of the first and second shrouds so as to form inner and outer plenums. Each inner plenum is defined between at least the junction and the substantially flat inner plate; each outer plenum is defined between at least the substantially flat inner plate and the outer plate. Each inner plenum is in fluid communication with a respective outer plenum through at least one of the cooling passages in the respective shroud.

Abstract: A turbine vane assembly which includes an outer endcap having a plurality of generally straight passages and passage segments therethrough, an inner endcap having a plurality of passages and passage segments therethrough, and a vane assembly having an outer shroud, an airfoil body, and an inner shroud. The outer shroud, airfoil body and inner shroud each have a plurality of generally straight passages and passage segments therethrough as well. The outer endcap is coupled to the outer shroud so that outer endcap passages and said outer shroud passages form a fluid circuit. The inner endcap is coupled to the inner shroud so that the inner end cap passages and the inner shroud passages from a fluid circuit. Passages in the vane casting are in fluid communication with both the outer shroud passages and the inner shroud passages. Passages in the outer endcap may be coupled to a cooling system that supplies a coolant and takes away the heated exhaust.