Patent ID: 7299618

Claim:
A gas turbine combustion apparatus having a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each of said combustors comprising a combustor inner tube and a combustor transition pipe, and comprising: one or more exhaust ports opening in said casing and communicating with an outside of said turbine casing chamber and having an exhaust pipe; one or more bleeding means for uniformly bleeding compressed air discharged into said turbine casing chamber; one or more recovery means for recovering compressed air bled by said bleeding means and discharging said compressed air to said exhaust ports; and exhaust control means for controlling an amount of exhaust which said recovery means discharge to said exhaust ports, wherein said recovery means is a circular pipe extending along said circumferential direction within said turbine casing chamber, and formed in a toroidal shape.