Patent ID: 8286416
Filing Date: 2012-10-16
Classification: F02K,F05D

Abstract:
1. A valve system intermediate a secondary flow path and a primary flow path of a gas turbine engine comprising: an engine core primary flow path; a fan flow secondary flow path coaxial with said primary flow path; a nozzle to eject said primary flow outside primary flow path; a frame including guides defining a passage between said primary flow path and said secondary flow path, said guides being mounted to an inner cooling liner structure of said inner engine core; and an arcuate plate slidable on an arcuate fashion on said guide between an open position permitting flow through said passage and a closed position locking flow through said passage, said arcuate plate located at a downstream end of said nozzle being moveable within said secondary flow path, and separating said secondary flow path from said primary flow path.