Patent ID: 8904799

Claim:
An annular combustor for a gas turbine engine for use in ground-based power generation, land or sea based vehicles or aircraft engines, the annular combustor comprises: a combustor, the combustor includes an outer shell, an inner shell, a front wall, and corrugations, the front wall connects the outer shell to the inner shell so as to form an annular volume arranged about a centerline of the combustor, the outer shell and the inner shell extend from the front wall to the corrugations and an annular discharge opening, the corrugations and the annular discharge opening are opposite to the front wall, the corrugations are spaced apart and circumferentially arranged about the centerline of the combustor and lead to the annular discharge opening, and the annular discharge opening is arranged about the centerline of the combustor; tangentially pointing and circumferentially spaced nozzles in the outer shell between the front wall and the corrugations and the annular discharge opening, the tangentially pointing and circumferentially spaced nozzles are for injecting combustion gas into the annular volume in tangentially circumferential directions for producing a flow of the combustion gas flowing through the annular volume from the front wall to the annular discharge opening in a first circumferential direction at a circumferential velocity; and the corrugations are circumferentially spaced and each of said corrugations extends along a path to the annular discharge opening that twists about the centerline of the combustor for interacting with the flow of the combustion gas flowing through the annular volume for turning the flow of the combustion gas flowing through the annular volume from the first circumferential direction to a second circumferential direction that is different from the first circumferential direction for accelerating the circumferential velocity of the flow of the combustion gas to the annular discharge opening.