Patent ID: 6134877
Filing Date: 2000-10-24
Classification: F05B,F23M,F23R

Abstract:
A combustor for a gas turbine engine in which a compressor supplies air to the combustor for cooling thereof and combustion therein, the combustor comprising:a) a radially inner member being of generally cylindrical formation and defining a combustion chamber,b) a radially outer member,c) a fuel/air mixer provided at an upstream end of the combustor as referred to a direction of flow of combustion products therethrough,d) said radially inner and outer members defining therebetween a cooling passage extending generally axially alongside the combustion chamber over at least part of a length thereof, the cooling passage having air inlet means comprising a plurality of inlets adjacent to a downstream end of the combustor for entry of air into the cooling passage from the compressor, the air flowing towards the mixer to cool the combustor and then entering the mixer to mix with fuel to provide a combustible mixture, the cross-sectional area of the cooling passage increasing over at least part of a length of the cooling passage in a direction from the downstream end to the upstream end of the combustion chamber,e) the formation of the radially inner member having a portion of reduced diameter at the upstream end affixed to the mixer, the reduced diameter portion being shaped to provide an annular chamber, andf) a sealing means in the annular chamber for sealing engagement with the mixer.