10 including in serial flow communication a fan section 14 a low pressure compressor 18 a high pressure compressor 22 a combustor 26 a high pressure turbine 30 and a low pressure turbine 34 the gas turbine engine 10 is circumferentially disposed about an engine centerline x during operation the fan section 14 intakes air and the compressors 18 22 pressurize the air the combustor 26 burns fuel mixed with the pressurized air the high and low pressure turbines 30 34 extract energy from the gases exiting the combustor 26 in a two spool design the high pressure turbine 30 utilizes the extracted energy from the hot combustion gases to power the high pressure compressor 22 through a high speed shaft 38 and a low pressure turbine 34 utilizes the energy extracted from the hot combustion gases to power the low pressure compressor 18 and the fan section 14 through a low speed shaft 42 the example method may be applied to other architectures such as a single spool axial design a three spool axial design and other architectures referring to the fig2 schematic there is shown an example turbo jet engine 50 the turbo jet engine 50 includes a fan section 54 a compressor section 58 a combustor section 62 a turbine section 66 an augmentor section 70 and a nozzle section 74 the compressor section 58 combustor section 62 and turbine section 66 are generally referred to as the core engine an axis a of the engine 50 is generally disposed and extends longitudinally through the.