Patent ID: 6951109

Claim:
A combustion liner assembly for a gas turbine comprising: a cap centerbody; a liner sleeve about said centerbody; a plurality of primary fuel nozzle cup assemblies within the liner sleeve and about the centerbody; a venturi downstream of the cap centerbody and nozzle cup assemblies and secured to said liner sleeve; said liner sleeve having an inlet for receiving dilution air into a plenum between the venturi and the liner sleeve for flow into a dilution zone downstream of the centerbody; said venturi defining a throat area downstream of the centerbody and including generally annular inner and outer sleeves spaced generally radially from one another; said venturi outer sleeve having a plurality of holes in communication with said plenum for flowing dilution air between the inner and outer venturi sleeves; said inner and outer sleeves of said venturi having wall portions extending in an axial upstream and radial direction toward said liner sleeve and terminating in respective overlapped flanges extending in a generally axial direction; and an annular weld about and sealing between the overlapped flanges to preclude dilution air leakage flow from said plenum.