Abstract: Provided is an aerodynamic profile for use in gas turbine airfoil and a turbine blade comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches. The R values are measured perpendicular to a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.

Abstract: A coolable airfoil having a passage for discharging particulates entrained in cooling air is disclosed. Various construction details are developed to provide clean cooling air to the leading edge of the airfoil. In one embodiment, a chordwise duct extends past a spanwisely extending supply passage to the inlet of a spanwisely extending rear passage such that momentum effects direct the flow of a portion of cooling air and particulates from the duct, past the entrance of the supply passage and into the rear passage and a larger portion of the flow of cooling air into the supply passage for cooling the leading edge of the airfoil.

Abstract: A stator vane (4) for a gas turbine engine having a varying chordal length (52, 54) is disclosed. The chordal length reduces a maximum (52) at a point intermediate the ends (40, 44) of the vane for defining a radially varying nozzle throat (58, 56) between adjacent vanes (4, 4a) in a stator vane stage.