Abstract: A method for cooling a stator vane is provided, comprising the steps of: (a) providing a hollow stator vane having a high pressure and a standard pressure chamber disposed within the hollow stator vane, adjacent the leading edge of the airfoil, and a supply chamber, disposed within the hollow stator vane, aft of the high and standard pressure chambers, and forward of the trailing edge; the stator vane further includes first and second inlet apertures, and first and second exit apertures; the first inlet apertures extend between the high pressure chamber and the supply chamber, and the second inlet apertures extend between the standard pressure chamber and the supply chamber; the first exit apertures extend between the high pressure chamber and the exterior of the stator vane, and the second exit apertures extend between the standard pressure chamber and the exterior of the stator vane; (b) determining the magnitudes of the gas flow pressure gradient facing the stator vane, and the position of the gradient rel

Abstract: Judiciously dimensioned slots in feather seals between adjacent edges of platforms of segmented stator vane for a gas turbine power plant serves to allow the flow of cooling air through the slots notwithstanding the feather seal shifting.

Abstract: A cooled rotor blade is constructed having a cooling passage extending from the root and through the airfoil shaped section in a serpentine fashion, making several passes between the bottom and top thereof; a plurality of openings connect said cooling passage to the trailing edge; a plurality of compartments are formed lengthwise behind the leading edge of the blade; said compartments having openings extending through to the exterior forward portion of the blade; and sized openings connect the cooling passage to each of the compartments to control the pressure in each compartment.