Northern Research & Engineering Corp.

Donald B Chouinard

Arnold M Heitmann

Walter L Brassert

A gas turbine includes a rotatable unit having a compression component and an expansion component, and a toroidal combustion chamber between the compression and expansion components. The gas turbine has a gas flow path serially through the compression component, the combustion chamber and the expansion component. A first bearing assembly is positioned on the side of the compression component remote from the combustion chamber and a second bearing assembly is positioned on the side of the expansion component remote from the combustion chamber so that the rotatable unit is unsupported between the compression and expansion components and no bearing structures are in the vicinity of the combustion chamber.

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Peabody, MA, United States of America

Donald B Chouinard