Patent ID: 8984891
Filing Date: 2015-03-24
Classification: F02C,F02K

Abstract:
1. An aircraft gas turbine engine comprising: a fan section, at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to a fan in the fan section, the row of FLADE fan blades radially extending across a FLADE duct circumscribing the fan section, an engine inlet including a fan inlet to the fan section and an annular FLADE inlet to the FLADE duct, a two dimensional flow FLADE air discharge fluid passage in fluid flow communication with the FLADE duct, a FLADE air discharge system including FLADE air upstream and downstream discharge slots in a divergent flap of a two dimensional exhaust nozzle of the engine and in fluid flow communication with the two dimensional flow FLADE air discharge fluid passage, and a valve for opening and closing the upstream and downstream discharge slots wherein the valve is operable for fully closing the upstream slot when the downstream slot is fully opened and fully opening the upstream slot when the downstream slot is fully closed.