Patent ID: 8230688

Claim:
An arrangement for delivering gasses from a plurality of combustors of a can annular gas turbine combustion engine to a turbine first stage section comprising a first row of turbine blades, the arrangement comprising a flow-directing structure for each combustor, wherein each flow-directing structure comprises a straight path portion for receiving a gas flow from a respective combustor, and an annular chamber end, wherein the respective annular chamber ends together define an annular chamber that is oriented concentric to a gas turbine engine longitudinal axis, for delivering the gas flow to the turbine first stage section; wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, in respective substantially uniform flow directions; wherein the annular chamber is configured to unite the respective straight gas flows to form a singular annular gas flow and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber.