Patent ID: 8007229
Filing Date: 2011-08-30
Classification: F01D,F04D,F05D,Y10T

Abstract:
1. A full ring vane nozzle for a gas turbine engine comprising: an inner vane ring with a multiple of inner apertures; an outer vane ring with a multiple of outer apertures; a multiple of fixed turbine vanes between said inner vane ring and said outer vane ring; and a multiple of rotational turbine vanes having a pocket and a spindle section along an axis of rotation, said multiple of rotational turbine vanes mountable between said inner vane ring and said outer vane ring, each of said multiple of rotational turbine vanes rotatable about said axis of rotation defined by a respective pair of said multiple of inner apertures and said multiple of outer apertures, said multiple of inner apertures and said multiple of outer apertures each sized to receive one of said multiple of rotational turbine vanes at an angle with respect to said inner vane ring and said outer vane ring.