Patent ID: 8365514

Claim:
A gas turbine engine comprising, at least in a first mode of operation: a core engine having, along a core flowpath: at least one compressor section; a combustor; and at least one turbine section; a fan upstream of the core flowpath and positioned to drive air downstream along the core flowpath and a bypass flowpath; and an auxiliary turbine engine comprising: an axial compressor; a fan having fan blades, a continuation of the bypass flowpath extending sequentially downstream through the axial compressor and radially outward through passageways in the blades of the fan of the auxiliary turbine engine, and a continuation of the core flowpath passing axially through the fan of the auxiliary turbine engine; a combustor downstream of the fan of the auxiliary turbine engine along the continuation of the bypass flowpath; and an axial turbine downstream of the combustor along the continuation of the bypass flowpath and comprising at least one stage of blades rotating with the fan of the auxiliary turbine engine.