Methods and apparatus to reduce turbine engine nozzle...

Power plants – Reaction motor – With thrust direction modifying means

Reexamination Certificate

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C060S771000, C239S265390, C239S265410

Reexamination Certificate

active

10696319

ABSTRACT:
A method facilitates assembling a flap system for a gas turbine engine exhaust nozzle including at least one backbone assembly. The method comprises providing a basesheet including a pair of circumferentially-spaced sides coupled together by an upstream side and a downstream side, forming at least one relief cut in the basesheet that extends at least partially across the basesheet from at least one of the circumferentially-spaced sides, and coupling the basesheet to the backbone assembly.

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