Patent ID: 6430932
Filing Date: 2002-08-13
Classification: F05B,F23R

Abstract:
A combustion liner assembly for use with industrial gas turbine engines comprising:a substantially cylindrical outer shell having a shell inlet end and a shell exit end, and a longitudinal axis defined therethrough, a premixing chamber for mixing fuel and air located adjacent said shell inlet end, a combustion chamber located between said premixing chamber and said exit end and in communication therewith, a plurality of tabs located near said shell inlet end for positioning said shell within a combustor, and a plurality of holes spaced around the circumference of said shell for introducing air into said shell; a cap assembly positioned within said shell inlet end for regulating the amount of air introduced into said premixing chamber, said cap assembly having receptacles for a plurality of fuel nozzles; a venturi assembly containing a cooling channel with at least one venturi inlet aperture for permitting cooling air to enter said venturi, and at least one venturi exit aperture for permitting cooling air to exit said venturi; a plenum having a radially outer surface, relative to said axis, of larger diameter than said outer shell and fixed to said outer shell at a first location between said shell inlet end and said plurality of holes and at a second location between said at least one venturi exit aperture and said shell exit end for directing cooling air exiting said at least one venturi exit aperture into said plurality of holes; and, a plurality of recesses located along the radially outer surface of said plenum.