number of vanes can potentially enhance mixing of the gases departing the combustion section thereby reducing the requirement for conservative cooling of downstream vanes thus an overall weight reduction may be achieved by reducing the requirements of cooling air in some embodiments additionally aerodynamic efficiency may be improved as an increased number of vanes can yield higher levels of unsteady flow in the downstream rotor passages as such the formation of rotor passage secondary flow vortices and losses can be inhibited referring now in detail to the drawings fig1 is a schematic diagram depicting an embodiment of a gas turbine engine 100 as shown in fig1 engine 100 includes a compressor section 102 a combustion section 104 and a turbine section 106 notably engine 100 is a turbofan although it should be noted that the concepts described herein should not be considered limited to use with gas turbine engines configured as turbofans turbine section 106 incorporates multiple stages each of which includes a set of stationary vanes and a corresponding set of rotating blades in this regard a first stage 108 of the turbine section includes a first set of vanes 110 and a first set of blades 112 the first stage of the turbine section is located immediately downstream of the combustion section and immediately upstream of a second stage 114 of the turbine which includes a second set of stationary vanes 116 as shown in fig2 blades 112 are located downstream of vanes 110 whereas vanes 116 are.