HYBRID IMPINGEMENT COOLED TURBINE NOZZLE

摘要

A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands (34, 32); (b) a hollow, airfoil-shaped turbine vane (30) extendi ng between the inner and outer bands, the interior of the vane (30) defining at least a forward cavity (54) and a mid-cavity (56) positioned aft of the forward cavity (54); (c) a hollo w impingement insert (60) received inside the mid-cavity (56), the impingement insert (60) having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane (30) at a radially outer end of the forward cavity (54) adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity (54) and a radially inner end of th e impingement insert (60).