Turbine nozzle with integral impingement blanket

摘要

A turbine nozzle segment includes: (a) an arcuate outer band segment (50); (b) a hollow, airfoil-shaped turbine vane (30) extending radially inward from the outer band segment (50); (c) a manifold cover (54) secured to the outer band such that the manifold cover (54) and the outer band segment (50) cooperatively define an impingement cavity; and (d) an impingement blanket (62) disposed in the impingement cavity, the impingement blanket (62) having at least one impingement hole formed therethrough which is arranged to direct cooling air at the outer band segment (50). A method is provided for impingement cooling the outer band segment (50).