TURBOFAN GAS TURBINE ENGINE WITH COMBUSTED COMPRESSOR BLEED FLOW

A gas turbine engine (20) includes a core section including a compressor (44, 50), a main combustor (54), and a main turbine (46, 52). Combustion products from the main combustor (54) drive rotation of the turbine (46, 52) and the compressor (44, 50). A power turbine (40) is fluidly connected to the main turbine (46, 52) and driven by exhaust from the main turbine (46, 52). The gas turbine engine (20) further includes a fan section (22) having a fan rotor (38) located fluidly upstream of the core section. The power turbine (40) is operably connected to the fan rotor (38) to drive rotation of the fan rotor (38) via rotation of the power turbine (40). The gas turbine engine (20) includes a bleed arrangement having one or more bleed passages (56) configured to divert a bleed airflow (62) from the compressor (44, 50) around the main combustor (54) and main turbine (46, 52), and reintroduce the bleed airflow (62) into the power turbine (40).