DUAL CYCLE INTERCOOLED ENGINE ARCHITECTURES

A gas turbine engine (300) includes a primary gas path (106) having, in fluid series communication: a primary air inlet (112), a compressor (104) fluidly connected to the primary air inlet (112), a combustor (108) fluidly connected to an outlet of the compressor, and a turbine fluidly connected to an outlet of the combustor (108). The turbine (116) is operatively connected to the compressor (104) to drive the compressor. A turbine cooling air conduit (372) extends from an air inlet of the turbine cooling air conduit (372) to an air outlet (376) of the turbine cooling air conduit (372).