Northern Research & Engineering Corp.

Donald N Chouinard

Arnold M Heitmann

Walter L Brassert

A gas turbine has a combustion chamber of toroidal configuration that includes separation structure dividing the combustion chamber into an annular primary zone and an annular dilution zone. Injection of compressor discharge air into the primary zone sets up a toroidal recirculation pattern of generally circular cross-sectional configuration. Fuel slinger structure at the inner periphery of the primary zone has a generally cylindrical surface for receiving and distributing fuel in a thin sheet for discharge in a radially outward direction as minute droplets towards the center of the toroidal recirculation pattern. The radial flow of the fuel droplets interacts with said toroidal recirculation pattern and provides intimate mixing of fuel and air, and resulting efficient combustion within said primary zone. The resulting combustion product flows from the primary zone past the separation structure into the dilution zone. Compressor discharge air injected into the dilution zone dilutes the products of combustion from the primary zone.

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Peabody, MA, United States of America

Donald N Chouinard