General Electric Company

Edward P Hopkins

Lewis Berkley Davis, Jr

Michael Alan Davi

Neil S Rasmussen

A stationary gas turbine combustor having a fuel nozzle and a combustion chamber receiving the fuel nozzle also contains a pressure wave interference element fixed within the interior of the combustor and disposed in the path of the variable pressure waves to modify the intensity of the pressure waves and the location of their nodes.

Acoustically tuned combustor

A nozzle is provided for a gas turbine combustion system in which the atomizing air metering nozzle is provided with an aerodynamically rotating orifice which turns air flow radially inward toward the source of oil or other liquid fuel prior to initiating a swirling vortex to eliminate centrifuging action of the air stream within the nozzle. Metering on the atomizing air vortex generating vanes are located at the exit of the vanes near the outer face of the fuel nozzle to eliminate entrapment of airborne particles. Vortex generator vanes are provided in the air stream path; these vanes lie on the surface of a cone which converges toward the nozzle exit. The vanes are at an angle to lines which would lie in a plane through the axis of the aforementioned cone along the surface of the cone, thereby to form a swirling air vortex at the nozzle exit.

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East Berne, NY, United States of America

Edward P Hopkins