Patent ID: 7836677

Claim:
At least one combustion apparatus and duct structure for a gas turbine engine comprising: at least one combustion apparatus comprising: a combustion system that receives fuel and air, ignites at least a portion of the fuel and air, and outputs a stream of first combustion products and any remaining fuel and air; and nozzle structure positioned adjacent to said combustion system, said nozzle structure comprising: an inlet that receives the first combustion products and any remaining fuel and air from said combustion system; an outlet that outputs the first combustion products and any remaining fuel and air; and a portion that accelerates the first combustion products and any remaining fuel and air from said combustion system in a direction substantially normal to a machine axis; and duct structure comprising: at least one entrance that receives the first combustion products and any remaining fuel and air from said at least one combustion apparatus; a cavity where any remaining fuel and air combust to generate second combustion products; and said duct structure comprising a shape that effects an acceleration of the first and second combustion products in a direction substantially parallel to the machine axis.