Williams International Co., L.l.c.

John Sordyl

Jamey J Condevaux

Lisa M Simpkins

A first orifice on a first inner surface of a first annular zone of a forward-bounded annular combustor provides for injecting air forward and radially outwards thereinto, from a location aft of a fuel slinger/injector. A radial dimension of a first outer surface of the first annular zone exceeds that of a corresponding first inner surface. A radial dimension of a second outer surface of a second annular zone of the annular combustor&#x2014;aft of the first annular zone&#x2014;exceeds that of a corresponding second inner surface. The first and second outer surfaces, and the first and second inner surfaces, are respectively coupled by transitional outer and inner surfaces of an annular transition zone located therebetween. The radial dimensions of the transitional outer and inner surfaces at the junctions with the corresponding second surfaces exceed the corresponding radial dimensions at the junctions with the corresponding first surfaces.

Combustion system

A rotary injector () comprising one or more radially-extending arms () provides for injecting fuel () into a combustion chamber (). The combustion chamber () receives air () from locations upstream and down-stream of the rotary injector (), and the arms () of the rotary injector () are adapted so that a pressure (P) in the combustion chamber () upstream of the rotary injector () is less than a pressure (P) in a plenum () supplying air () to the combustion chamber () upstream of the rotary injector ().

Gas turbine engine rotary injection system and method

Fuel and air are injected in a first poloidal flow in a first poloidal direction within a first annular zone of an annular combustor. A first combustion gas from the at least partial combustion of the fuel and air is discharged into an annular transition zone of the annular combustor and transformed to a second combustion gas therein within an at least partial second poloidal flow followed by an at least partial third poloidal flow in the annular transition zone, wherein the direction of the second poloidal flow is opposite to that of the first and third poloidal flows. The second combustion gas is discharged into a second annular zone of the annular combustor, and then transformed to a third combustion gas therein before being discharged therefrom, responsive to which a back pressure is generated in the annular combustor.

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Northville, MI, United States of America

John Sordyl