will be described in relation to a gas turbine engine this description is exemplary only and not intended to be limiting in any way fig2 illustrates a view of an exemplary multi staged axial compressor 118 that may be used in gas turbine engine as shown the compressor 118 may include a plurality of stages each stage may include a row of compressor rotor blades 120 followed by a row of compressor stator blades 122 thus a first stage may include a row of compressor rotor blades 120 which rotate about a central shaft followed by a row of compressor stator blades 122 which remain stationary during operation the compressor stator blades 122 generally are circumferentially spaced one from the other and fixed about the axis of rotation the compressor rotor blades 120 are circumferentially spaced about the axis of the rotor and rotate about the shaft during operation as one of ordinary skill in the art will appreciate the compressor rotor blades 120 are configured such that when spun about the shaft they impart kinetic energy to the air or working fluid flowing through the compressor 118 as one of ordinary skill in the art will appreciate the compressor 118 may have many other stages beyond the stages that are illustrated in fig2 each additional stage may include a plurality of circumferential spaced compressor rotor blades 120 followed by a plurality of circumferentially spaced compressor stator blades 122 fig3 illustrates a partial view of an exemplary turbine section.