Patent ID: 7886545
Filing Date: 2011-02-15
Classification: F23R,Y10T

Abstract:
1. A method for assembling a gas turbine combustor system, said method comprising: providing a combustion liner including a center axis, an outer wall, a first end, and a second end, wherein the outer wall orientated substantially parallel to the center axis and having a first end and a second end having substantially the same cross-sectional area; coupling a transition piece to the liner second end, wherein the transition piece includes an outer wall having a first end with a first cross-sectional area and a second end with a second cross-sectional area such that the transition piece is substantially frustoconical in shape; and coupling a plurality of lean-direct injectors along the liner outer wall and the transition piece outer wall such that the injectors are spaced axially apart along the liner outer wall and the transition piece outer wall.