Patent ID: 6745570
Filing Date: 2004-06-08
Classification: F02K,F05D,Y10S,Y10T

Abstract:
A method for assembling a flap system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies, said method comprising: providing a flap basesheet having a width defined between a pair of side edges that are coupled together by a leading edge and a trailing edge, and including at least one stiffener that extends between the basesheet side edges and includes an intermediate portion that has a width that is smaller than that of the basesheet and is at least one of bonded to and formed integrally with the basesheet; and forming a first slot in the stiffener that extends from the basesheet first side edge through the stiffener to the stiffener intermediate portion; and forming a second slot in the stiffener that extends from the basesheet second side edge through the stiffener to the stiffener intermediate portion; and coupling the basesheet to the gas turbine engine with a backbone assembly.