58 specifically transition duct 80 includes a plurality of panels 82 coupled together circumferentially such that a flow passageway 84 is defined through transition duct 80 between high pressure turbine 18 and low pressure turbine 20 accordingly panels 82 extend generally axially between an upstream end 86 of transition duct 80 and a downstream end 88 of duct 80 low pressure turbine 18 includes a plurality of stages 90 and each stage includes a row of circumferentially spaced rotor blades 92 and a row of circumferentially spaced stationary vanes 94 in the exemplary embodiment turbine 20 is coupled in axial flow communication to turbine 18 and is substantially concentrically aligned with respect to turbine 18 a casing 96 extends circumferentially around turbine 20 more specifically casing 96 extends downstream from extension duct 80 to a turbine rear frame 100 turbine rear frame 100 is annular and extends between casing 96 and a primary exhaust nozzle 102 a bypass system 110 is coupled in flow communication to compressor 14 and downstream from compressor 14 such that a portion of flow discharged from compressor 14 is channeled through bypass system 110 as is described in more detail below in the exemplary embodiment bypass system 110 is coupled between high and low pressure turbines 18 and 20 respectively and more specifically between a pair.