Patent ID: 8127528

Claim:
A gas turbine engine comprising: a core engine comprising: a high pressure compressor having a core driven fan stage; a high pressure turbine; a high pressure shaft connecting the high pressure compressor with the high pressure turbine; and a main combustor disposed between the high pressure turbine and the high pressure compressor; a low pressure spool and comprising: a low pressure fan disposed upstream of the high pressure compressor, a low pressure turbine disposed downstream of the high pressure turbine, and a low pressure shaft connecting the low pressure fan with the low pressure turbine; a main bypass duct circumscribing the core engine configured to receive discharge from the low pressure fan; a peripheral duct circumscribing the main bypass duct configured to receive unpressurized inlet air; an auxiliary power system positioned within the peripheral duct, the auxiliary power system comprising: a peripheral combustor; and a plurality of airfoil blades including turbine portions and fan portions; and a bleed duct extending from the high pressure compressor, through the main bypass duct such that flow through the bleed duct is segregated from flow through the main bypass duct, and directly into the peripheral combustor.