Patent ID: 6286302
Filing Date: 2001-09-11
Classification: F23D,F23L,F23R

Abstract:
A combustion apparatus for a gas turbine engine, comprising:(a) a combustor structure including at least one combustion chamber;(b) a dual cone fuel nozzle for injecting both fuel and water to said combustion chamber; and(c) a swirl cup package upstream of and adjacent to said combustion chamber, said swirl cup package further comprising:(1) a swirler; and(2) a venturi extending between said nozzle and said combustion chamber for mixing said and water with air;wherein said venturi is configured without a heat shield along an inner surface thereof and has a varying thickness from an upstream end to a downstream end resulting in a heat transfer conduction path that reduces axial stresses imposed on said venturi when water impinges on an upstream portion of said venturi.