Hot Spike Mixer.
DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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This patent discloses 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. Author
- Fluid Mechanics
- Jet and Gas Turbine Engines