Patent ID: 6098400
Filing Date: 2000-08-08
Classification: F02K,F05D

Abstract:
A gas turbine engine nozzle including a divergent petal articulated on a front edge to a convergent petal by a first cylindrical joint and articulated at an intermediate point between the front edge and a rear edge of the divergent petal to a compression bar by a second cylindrical joint, the first and second cylindrical joints being arranged perpendicular to an engine axis, the divergent petal comprising:a base plate having a front edge, a back edge, and a back side;at least one stiffening fin attached to and extending longitudinally along the back side of said base plate, said stiffening fin having a front hole and an intermediate slotted hole defined laterally therein;a traction bar positioned on the back side of said base plate and including rear lugs with holes defined therein; said traction bar being linked to the convergent petal and the compression bar by the first and second cylindrical joints, respectively; the base plate being related to said traction bar by the first cylindrical joint perpendicular to the engine axis, coincident with a joint between the convergent and divergent petals; and a sliding joint between the slotted holes and the holes in the rear lugs of said traction bar and coincident with the second cylindrical joint between said traction bar and the compression bar, displacement of the sliding joint being functionally parallel to said base plate.