rotate with rotor blades in still further embodiments the non axisymmetric flow members may be placed in a flow path downstream of a centrifugal compressor in other embodiments certain non axisymmetric flow members disposed within the duct may be actuated to extend or retract while others remain passive during the entire operation of a gas turbine engine some non axisymmetric flow members may have a larger peak bump distance than others still others may have different locations of peak bump distance relative to the leading or trailing edge of the non axisymmetric flow members still other non axisymmetric flow members disposed within a duct may have varying shapes and sizes in still other embodiments a gas turbine engine is provided comprising an inner wall member an outer wall member spaced from the inner wall to define a fluid flowpath a compressor including a guide vane stage located upstream from the fluid flowpath the guide vane stage including a plurality of vanes positioned around a portion of the fluid flowpath and a plurality of elongated protrusions located downstream of the guide vane stage and extending into the fluid flowpath in a further embodiment an apparatus is provided comprising a fluid flowpath a compressor stage located upstream from the fluid flow path a plurality of guide vanes positioned circumferentially around a portion of the fluid flowpath and a plurality of restrictors located in the fluid flowpath for preventing separated flow downstream of the guide vanes in still another embodiment an apparatus is provided comprising a gas turbine engine having a duct configured to support a fluid flow a vane disposed within the duct and means for altering the diffusion of the fluid flow downstream of the vane in still a further embodiment a method is provided.