a low pressure compressor 14 a high pressure compressor 16 a combustor 18 a high pressure turbine 20 and a low pressure turbine 22 the gas turbine engine 10 is circumferentially disposed about an engine centerline x during operation air is pulled into the gas turbine engine 10 by the fan section 12 pressurized by the compressors 14 16 mixed with fuel and burned in the combustor 18 hot combustion gases generated within the combustor 18 flow through high and low pressure turbines 20 22 which extract energy from the hot combustion gases in a two spool configuration the high pressure turbine 20 utilizes the extracted energy from the hot combustion gases to power the high pressure compressor 16 through a high speed shaft 24 and the low pressure turbine 22 utilizes the energy extracted from the hot combustion gases to power the low pressure compressor 14 and the fan section 12 through a low speed shaft 26 the present disclosure however is not limited to the two spool configuration described and may be utilized with other configurations such as single spool or three spool configurations or gear driven fan configurations gas turbine engine 10 is in the form of a high bypass ratio turbine engine mounted within a nacelle or fan casing 28 which surrounds an engine casing 30 housing an engine core.