Patent ID: 7966828
Filing Date: 2011-06-28
Classification: F02K,F05D,Y02T

Abstract:
1. A gas turbine engine system comprising: a nacelle; a gas turbine engine within the nacelle; a fan bypass passage between the nacelle and the gas turbine engine; a nozzle section comprising members that are woven together and comprising gaps between said members that are woven together, wherein said gaps are closed when said nozzle section is a first axial length and open when said nozzle section is a second axial length wherein the nozzle section is associated with the fan bypass passage to influence flow through the fan bypass passage, wherein the nozzle section is selectively adjustable along a central axis between the first axial length and the second axial length that is larger than the first axial length to influence the flow; and a controller for selectively moving the nozzle section responsive to one of a plurality of operational states of the gas turbine engine.