Patent ID: 6398129
Filing Date: 2002-06-04
Classification: B64D,F02K,Y02T

Abstract:
A convergent/divergent nozzle of an axisymmetrical exhaust nozzle for a gas turbine engine including a hinged pivot at the juncture of where the convergent portion and the divergent portion of said nozzle meet, said convergent nozzle comprising a plurality of circumferentially spaced axially extending flaps and said divergent nozzle having a plurality of circumferentially spaced axially extending flaps, a radius throat having a surface exposed to the working medium of the gas turbine engine and being located at the juncture of the hinged pivot, the surface of said radius throat being defined by a convex curvature formed on the flaps of the divergent nozzle and falling in the range of from 2 inch radius to 10 inch radius.