Abstract: An apparatus and method are provided for cooling the rotating blades in the turbine section of a gas turbine. Cooling of the leading edge is accomplished by forming a radial passageway in the leading edge portion of the blade airfoil. Rows of holes along the leading edge of the blade airfoil allow cooling air to flow from the radial passageway to the surface of the leading edge, thereby cooling the leading edge portion of the airfoil. The flow area of the radial passageway reduces as it extends radially outward so that the velocity of the cooling air flowing through the passageway is maintained. A plenum formed in the root portion of the blade distributes cooling air to small diameter holes in the center and trailing edge portion of the airfoil.

Abstract: An apparatus and method is provided for locking side entry blades, in a rotor, such as used in compressors, turbines and fans. The apparatus utilizes arcuate locking devices retained in a circumferential groove in the periphery of the rotor. Each locking device features a key which engages a keyway in the side of the blade root shank. Use of the locking devices does not require that the blades having abutting platforms.

Abstract: A structure for the root portion of a turbine blade and for the attachment grooves on a turbine rotor in conjunction with blades having integral shrouds and platforms as well as blades which are not attached to one another, blades which are joined by nonintegral shrouds and blades which do not include platforms. The invention is applicable to straight side entry blade roots and rotor grooves as well as curved side entry blades and curved rotor grooves. The invention results in reduced stress levels in the blade attachment structure by decreasing the land widths and increasing the fillet radii of curvature associated with each tang on a turbine blade root. In addition, the fillet radii of curvature are individually dimensioned to more uniformly distribute stress levels among blade root tangs. The reduction in land widths is accomplished by increasing land contact stresses for a given blade design.

Abstract: A stationary blade assembly with a segmented inner shroud to permit radial expansion and contraction of the blades and circumferential expansion and contraction of the shroud segments and a seal plate which fits into a circumferential groove in the shroud segments and is held therein by pinned keys which slide in kerfs in the outer edge of the seal plate and a labyrinth seal strip disposed in a circumferential groove in the inner edge of the seal plate to provide a small clearance seal not affected by thermal gradients.