Patent ID: 6032457
Filing Date: 2000-03-07
Classification: F23R,Y02T

Abstract:
In a combustor for a gas turbine engine, said combustor comprising a combustion chamber defined at one end thereof by a bulkhead having an opening therein, said bulkhead being thermally insulated from said combustion chamber by a bulkhead heat shield, said bulkhead further comprising a fuel nozzle and fuel nozzle guide structure therefor and a retainer for securing said fuel nozzle and said fuel nozzle guide structure within said bulkhead opening, said fuel nozzle guide comprising:(a) an annular bushing sized for receiving said fuel nozzle, said bushing having a first end and a second end, said first end being connected to said retainer;(b) a flange extending radially from said second end of said bushing, said flange having a proximal portion spaced proximal to said bashing, and a distal portion spaced distal from said bushing, said distal portion extending substantially parallel to said bulkhead heat shield; and(c) a plurality of radially extending ribs disposed about said distal portion of said flange, each of said ribs having leading ends and trailing ends, said trailing ends being arcuate in shape;(d) wherein said ribs are of sufficient number to substantially eliminate vortices as film cooling air passes between said ribs.