Patent ID: 8418471
Filing Date: 2013-04-16
Classification: F02K,F05D

Abstract:
1. A method of varying flow through a pylon nozzle exit area of a gas turbine engine comprising the steps of: (A) varying a variable area flow system in communication with a flow passage through an engine nacelle pylon to change a volume of bypass flow through the engine nacelle pylon and control flow through a pylon nozzle exit area in response to a flight condition, said variable area flow system movable toward an open position to increase flow through said pylon nozzle exit area and toward a closed position to decrease flow through said pylon nozzle exit area (B) having at least one bifurcation that has a variable pylon intake and a variable pylon exhaust, wherein said variable pylon intake comprises a plurality of turning vanes having variable heights relative to each other; and (C) forming the flow passage as an internal passage within a body of the bifurcation, with the internal passage extending from the variable pylon intake to the variable pylon exhaust.