Patent ID: 8839626
Filing Date: 2014-09-23
Classification: F01D,F05D,F23R

Abstract:
1. A gas turbine combustor comprising: a fuel nozzle for injecting mixed gas of fuel and air, a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber, a liner flow sleeve arranged on the concentric circle with the liner on the outer periphery side of the liner, a transition piece which is a flow path for leading combustion gas generated in the liner to turbine blades, and a transition piece flow sleeve for wrapping an outside surface of the transition piece for flowing air through the gap between the liner and the liner flow sleeve, the transition piece flow sleeve having a portion surrounding an outlet portion of the transition piece, wherein the outlet portion of the transition piece has a plurality of corner portions, wherein a plurality of air introduction holes for introducing air into the transition piece flow sleeve are formed over the entire region portion of the transition piece flow sleeve excluding the corner portions of the transition piece flow sleeve in a sectional direction thereof.