TURBINE ENGINE BLEED WASTE HEAT RECOVERY

A gas turbine engine assembly includes a core engine that includes a core flow path (C) where a core airflow (25) is compressed in a compressor section (24), communicated to a combustor section (26), mixed with fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section (28), a first tap (66) at a location up stream of the combustor section (26) for communicating a portion of the core airflow (25) as a bleed airflow downstream of the combustor section (26), a heat exchanger (64) that places the bleed airflow that is communicated from the first tap (66) in thermal communication with the high energy combusted gas flow downstream of the combustor section (26), and a power turbine (72) that is configured to generate shaft power from expansion of the heated bleed airflow, the power turbine (72) includes an inlet (84) that is configured to receive the heated bleed airflow from the heat exchanger (64).