shape 30 which in accordance with an exemplary embodiment is configured for enhanced turbine performance a list of x y and z coordinates or points for airfoil core shape 30 is presented in table i and meets compressor requirements for interaction between adjacent stages aerodynamic efficiency and provides an improved aeromechanics margin over prior shapes moreover the particular airfoil core shape 30 in accordance with the exemplary embodiment meets system requirements for flow dynamics loading and frequency response the points are arrived at by iteration between aerodynamic and mechanical design improvements and are the only loci of points that allow turbomachine 2 to operate in an efficient smooth manner as will become more fully evident below airfoil core shape 30 is represented as a set of 3024 points listed in table 1 the 3024 points represent 27 airfoil sections each containing 112 points of which 24 sections comprise airfoil core shape 30 the x y and z coordinates which represent a profile of airfoil core shape 30 are created in a coordinate system which is defined relative to a cold engine part the origin of the coordinate system on the cold centerline axis is x 0 0 y 0 0 and z 0 0 the z coordinate axis is defined as a radial line from the y coordinate axis the x coordinate axis is defined as being normal to a plane defined by the y z axis the airfoil sections are cut normal to the z coordinate axis x and y points which make up the airfoil core profile shape at each section are in inches the radial z values in inches for the section planes have an origin of z 0 the radial distance between each section varies however a total radial distance of airfoil core shape 30.