Abstract: A venturi assembly for a turbine combustor includes a first outer annular wall and a second intermediate annular wall radially spaced from each other in substantially concentric relationship. The first outer annular wall and said second intermediate annular wall shaped to define a forward, substantially V-shaped throat region, and an aft, axially extending portion. A third radially innermost annular wall is connected to the second intermediate annular wall at an aft end of said throat region. A first plurality of apertures is provided in the first outer annular wall in the substantially V-shaped throat region, and a second plurality of apertures is provided in the aft, axially extending portion of said second intermediate annular wall so that cooling air flows through the first and second pluralities of apertures to impingement cool the third radially innermost annular wall.

Abstract: A fuel nozzle for a gas turbine includes an annular passage configured to flow a fuel and a disk concentric with and disposed at a second end of the annular passage. The disk extends radially outward from the second end. A plurality of passages extend through the disk and are configured to impart swirl to a working fluid flowing through the passages. A shroud including an upstream end axially separated from a downstream end surrounds the disk and extends downstream from the disk.

Abstract: A venturi assembly for a turbine combustor includes a first outer annular wall and a second intermediate annular wall radially spaced from each other in substantially concentric relationship. The first outer annular wall and said second intermediate annular wall shaped to define a forward, substantially V-shaped throat region, and an aft, axially extending portion. A third radially innermost annular wall is connected to the second intermediate annular wall at an aft end of said throat region. A first plurality of apertures is provided in the first outer annular wall in the substantially V-shaped throat region, and a second plurality of apertures is provided in the aft, axially extending portion of said second intermediate annular wall so that cooling air flows through the first and second pluralities of apertures to impingement cool the third radially innermost annular wall.

Abstract: A combustor includes a combustion chamber and a liner surrounding the combustion chamber. A ridge on top of the liner extends continuously around the liner. In alternate embodiments, a ridge extends continuously around the liner, and a groove extends continuously around the liner adjacent to the ridge, wherein both of the ridge and the groove are either substantially flat or curved.