Patent ID: 6070407
Filing Date: 2000-06-06
Classification: F02K

Abstract:
A ducted fan gas turbine engine having a primary fan duct having a downstream end, a core gas generator having a nozzle portion and including a secondary cowl at least partly within the downstream end of the primary fan duct and radially spaced from the core gas generator so as to define a secondary fan duct, said primary fan duct having an outlet area that is fixed and means for selectively diverting fan air which would normally flow through said secondary duct to an exit nozzle thereof, into another path or paths for exit from a nozzle or nozzles other than that of said secondary duct, said engine having an axis and said fan air diversion means comprising the nozzle portion of the core gas generator of said engine, said nozzle portion being translatable axially of the engine and relative to said secondary cowl and being so proportioned as to substantially block the exit nozzle thereof when translated to a fully retracted position.