Patent ID: 6279323
Filing Date: 2001-08-28
Classification: F23R,Y02T

Abstract:
A gas turbine engine combustor comprising:radially outer and inner annular liners joined at forward ends to an annular dome and spaced radially apart at aft ends to define an annular outlet;a swirl cup mounted to said dome and including a flare cone extending through said dome with an obtuse first flare angle for discharging fuel in a wide spray from an outlet thereof;a flared heat shield having a tubular inlet end surrounding said flare cone and extending in major part aft from said outlet thereof with an obtuse second flare angle offset forwardly from said first flare angle at said cone outlet to define a radially outwardly facing step protruding said cone outlet axially aft from said heat shield between said first and second cone angles thereof; andsaid flare cone and heat shield being discrete components unattached at said step to permit unrestrained differential movement therebetween.