Patent ID: 6865892

Claim:
A gas turbine combustor having a first combustion chamber in fluid communication with a second combustion chamber, said combustor comprising: a venturi assembly comprising: a first venturi end proximate said first combustion chamber and a second venturi end proximate said second combustion chamber; a flowpath wall extending from said first venturi end to said second venturi end and having a first outer band, first convergent wall, first divergent wall, said first convergent wall abutting said first divergent wall at a first throat, a first annular wall extending from said first divergent wall, and a blocking ring fixed to said first annular wall, said first outer band having a first band diameter, a second band diameter, and a first thickness therebetween, said first throat positioned axially between said first and second combustion chambers; a passageway wall having a second convergent wall, a second divergent wall, and a second annular wall in spaced relation to and radially outward of said flowpath wall thereby forming a first passageway there between; a plurality of first holes spaced circumferentially about said first outer band, said first holes in fluid communication with said first passageway; an upper liner generally annular in shape having a first upper end, a second upper end, a first upper diameter, and a second upper diameter, said first upper diameter and said second upper diameter proximate said second upper end defining a second thickness there between, a plurality of second holes circumferentially spaced about said upper liner and in fluid communication with said first holes and a second passageway radially outward of said upper liner; a lower liner generally annular in shape having a first lower end, a second lower end, a first lower diameter, and a second lower diameter, said first lower diameter and said second lower diameter proximate said first lower end defining a third thickness there between, a plurality of third holes circumferentially spaced about said lower liner proximate said second venturi end, said third holes in fluid communication with said first passageway; and, a cap assembly for securing a plurality of fuel nozzles to said combustor, said cap assembly fixed to said upper liner proximate said first upper end; wherein said venturi assembly is secured to said upper liner and said lower liner in an easily removable manner by a plurality of retaining pins such that said first outer band of said venturi is located radially within said upper liner and said upper liner is located radially within said lower liner.