Hot spike mixer
AssigneeThe United States of America as represented by the Secretary of the Air Force
InventorDavid L. Wright
Life of this patent
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Abstract
A mixer at the exit opening of a high performance jet engine to prevent premature migration of the core flow into the duct stream thereby operating to eliminate hot streaks in the augmentor and nozzle areas during augmentation. The mixer consists of a concave fillet positioned on the pressure side of the turbine exit guide vane and exhaust case at the trailing edge.
Claims1
A hot spike mixer for installation on a turbine exit guide vane at an outer portion of a turbine exhaust case of a high performance jet engine to prevent the premature migration of the core flow into a duct stream, said turbine exit guide vane having a lower portion, a pressure side and a suction side, said mixer comprising a concave fillet positioned on the pressure side of the turbine exit guide vane at a downstream end thereof, said concave fillet including a flow ramp having a small inner end upstream and a large outer end terminating at said outer portion of the turbine exhaust case, said concave fillet being positioned between said lower portion of the turbine exit guide vane and the turbine exhaust case thereby preventing the formation of hot streaks in augmentor and nozzle areas of the jet engine caused by the premature migration of core flow into the duct stream.
Dependencies are inferred from the claim text.