Patent ID: 8371812

Claim:
A turbine frame assembly for a gas turbine engine, comprising: (a) a turbine frame including: (i) an outer ring; (ii) a hub; (iii) a plurality of struts extending between the hub and the outer ring; (b) a plurality of two-piece strut fairing fairings, each surrounding one of the struts, each strut fairing comprising: (i) an inner band; (ii) an outer band; and (iii) an airfoil-shaped vane extending between the inner and outer bands; and (c) a plurality of nozzle segments disposed between the outer ring and the hub and disposed circumferentially between adjacent ones of the struts, each nozzle segment being an integral metallic casting including: (i) an arcuate outer band; (ii) an arcuate inner band; and (iii) an airfoil-shaped vane.