Patent ID: 8453458

Claim:
A gas turbine engine having an exhaust arrangement, the exhaust arrangement comprising: a core exhaust having a shaped center and an exit nozzle about the shaped center arranged to define a passage therebetween, a bypass duct arranged so as to define an exhaust nozzle about the exit nozzle, the core exhaust and bypass duct defining a mixing plane having a cross-section that includes: i) a first cross sectional area between the shaped center and the exit nozzle and (ii) a second cross sectional area between the exit nozzle and the bypass duct, wherein when the gas turbine engine is viewed in a cross section, the mixing plane transects at least a portion of the shaped center; and the mixing plane is; i) substantially perpendicular to a longitudinal axis of the gas turbine engine, and ii) located upstream of an exhaust nozzle exit, an axial displacement mechanism configured to extend along a longitudinal axis of the gas turbine engine to cause relative displacement of the exit nozzle relative to the shaped center and bypass duct so as to vary the ratio of the mixing plane area between the first and second cross sectional areas, so as to vary the first and second cross sectional areas.