An Augmented Combustion Chamber Using Vorbix Principle with Core Stream Swirl.
DEPARTMENT OF THE NAVY WASHINGTON DC
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The present invention relates to vortex burning and mixing VORBIX augmentors for aircraft engines, and more particularly to a VORBIX augmentor using core stream swirl. Accordingly, the present invention provides a VORBIX augmentor with core stream swirl. Means for swirling the core stream are situated upstream from the augmentor area to promote mixing of core and pilot flows. Such swirling means is provided by a redesigned turbine exit guide vane which produces an approximately 20 deg off axial swirl flow entering the augmentor area.
- Jet and Gas Turbine Engines