as shown in fig1 - 4 , a turbomachine 2 constructed in accordance with an exemplary embodiment includes a compressor portion 4 and a turbine portion ( not shown ). compressor portion 4 is enclosed by a compressor housing 6 and has an axial flow path 8 . compressor portion 4 includes a plurality of variable and stationary vanes , and moving rotor blades two of which are shown at 18 and 20 respectively . compressor portion 4 is also shown to include additional compressor stages ( not separately labeled ) the number of which can vary depending upon compressor make and model . among the stationary vanes 18 is stator “ 0 ” or a first stage compressor stator vane 22 for 7f , 7fa , 7fa +, 7fa + e gas turbine frames . in the exemplary embodiment shown , first stage compressor stator vane 22 includes an airfoil core shape 30 having first and second ends 34 and 36 . first end 34 is provided with a base member 38 that serves as an anchor point . more specifically , base member 38 is a dovetail portion that interfaces with a second dovetail slot ( not shown ) to locate it in the compressor flow path . airfoil core shape 30 has a profile including a three dimensional ( 3 - d ) shape that defines a suction side 44 and a pressure side 46 as well as a leading edge 49 and a trailing edge 48 . an important aspect of first stage compressor stator vane 22 is airfoil core 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 is 15 . 4294 inches . the bottom and top sections z o and z 1 , may be obscured by cast - in features , such as base member 38 , that are not included in the x , y , and z points that define airfoil core shape 30 . all of the 3024 points are taken from a nominal cold or room temperature for each airfoil section of airfoil core shape 30 . each airfoil section is joined smoothly with adjacent airfoil sections to form the airfoil core shape 30 . it should be appreciated that as each compressor stator vane 22 heats up during operation of compressor portion 4 , the airfoil core profile shape will change as a result of stress and temperature . thus , the x , y and z points are provided at cold or room temperature for manufacturing purposes . since the manufactured airfoil core shape may be different from a nominal airfoil core shape defined in table 1 , a tolerance of + 0 . 160 and − 0 . 0 inches from the nominal profile is allowed and thus defines an overall design envelope for airfoil core shape 30 . the overall design is robust to this design envelope without impairment of mechanical or aerodynamic properties of first stage compressor stator vane 22 . it should also be appreciated that the airfoil core shape 30 can be scaled up or scaled down geometrically for introductions into similar turbine designs , with smaller or larger frame sizes . consequently , the x , y , and z coordinates in inches may be multiplied or divided by the same constant or number / factor to provide a scaled up or scaled down version of first stage stator vane 22 while retaining the airfoil core profile shape and unique properties . as best shown in fig2 , a coordinate system for airfoil core shape 30 in accordance with exemplary embodiment is indicated generally at 100 . as discussed above , coordinate system 100 is defined relative to a cold stator vane . coordinate system 100 includes an x - axis 105 , a y - axis 110 , and a z - axis 115 . the origin of coordinate system 100 is centered on a point located first stage compressor stator vane 22 covered by base member 38 . x - axis 105 is directed axially along a centerline axis ( not separately labeled ) of turbomachine 2 and z - axis 115 is directed along a radial line normal to the centerline axis . the positive direction of x - axis 105 , y - axis 110 , and z - axis 115 is identified by label placement in fig2 . as best shown in fig3 and 4 , airfoil core shape 30 includes a plurality of sections 150 - 172 . section 150 is located at z 0 and the airfoil core shape 30 extends through sections 172 before terminating at section 180 located at z 1 . as discussed above , sections 150 - 172 , and 180 are cut normal to z c - axis 115 . the x and y coordinates which make up each section are presented in table 1 are in inches . fig5 illustrates a set of 112 points 200 which make up section 151 . fig6 illustrates a design envelope for airfoil core shape 30 . the x , y , and z values listed in table 1 illustrate ideal point location for each point of each section of airfoil core shape 30 . however , there exist variations from the ideal point location attributed to manufacturing tolerances and the like which must be taken into account . thus , a design envelope is established which sets forth an acceptable outer boundary or distance from a nominal profile 250 for each section 150 - 172 , and 180 . therefore it should be understood that each x , y , and z point includes a tolerance or ± value . in consideration of process capability , a tolerance 260 of + 0 . 160 inches is allowed in the formation of airfoil core shape 30 . tolerance 260 includes an upper limit 270 defined as a 0 . 160 - inch deviation from nominal profile 250 and a lower limit 280 , defined as a − 0 . 000 - inch variation from nominal profile 250 . the design envelope or tolerance 260 is robust such that this variation does not impair mechanical and aerodynamic performance of compressor stator vane 22 . in no way limiting of the exemplary embodiment , airfoil core shape 30 provides an increased efficiency as much as 0 . 15 % compared to previous individual airfoil core shapes for first stage compressor stator vane 22 . moreover , and in no way limiting of the exemplary embodiment , in conjunction with other airfoil core shapes , which are conventional or enhanced ( similar to the enhancements herein ), airfoil core shape 30 , as embodied by the invention , provides an increased efficiency as much as 0 . 15 % compared to previous individual sets of airfoil core shapes for first stage compressor stator vane 22 . this increased efficiency provides , in addition to the above - noted advantages , a power output with a decrease the required fuel , therefore inherently decreasing emissions to produce energy . of course , other such advantages are within the scope of the exemplary embodiment . at this point it should be understood that the points disclosed in table 1 are exemplary , variations / deviations from the points in table 1 at one or more sections that do not substantially affect the desired properties obtained by the airfoil core shape of the exemplary embodiments fall within the scope of the exemplary embodiments of the invention . while the invention has been described in detail in connection with only a limited number of embodiments , it should be readily understood that the invention is not limited to such disclosed embodiments . rather , the invention can be modified to incorporate any number of variations , alterations , substitutions or equivalent arrangements not heretofore described , but which are commensurate with the spirit and scope of the invention . additionally , while various embodiments of the invention have been described , it is to be understood that aspects of the invention may include only some of the described embodiments . accordingly , the invention is not to be seen as limited by the foregoing description , but is only limited by the scope of the appended claims .