Patent ID: 7730714

Claim:
A turbofan gas turbine engine comprising: a forward fan section including at least one row of circumferentially spaced apart longitudinally forward fan rotor blades; a core engine located aft and downstream of the forward fan section and including in downstream serial flow relationship a core compressor, a core combustor, and a high pressure turbine drivingly connected to the core compressor by a core engine shaft; a fan bypass duct located downstream of the forward fan section and disposed radially outwardly of the core engine; the forward fan section located axially forward and upstream of a radially outer inlet of the fan bypass duct; an exhaust duct downstream of and in fluid communication with the core engine; a fan bypass duct outlet from the fan bypass duct to the exhaust duct downstream of the core engine; and the forward fan section having only a single stage of fan guide vanes and the fan guide vanes being variable fan outlet guide vanes located downstream of and adjacent to the forward fan rotor blades, for adjusting the flow into the fan duct.