A 4.4 in diameter circular ejector was tested to determine the effect on thrust augmentation ratio of the primary nozzle height and injection angle. Also tested were the effects of alternating primary nozzle injection angles, diffuser blowing and suction, inlet cross flow and low primary nozzle exit velocities on thrust augmentation. The results showed that both the primary nozzle injection angle and height affect the maximum thrust augmentation ratio attainable. A small amount of cross flow at the inlet increased the maximum thrust augmentation. The alternating primary nozzle injection angle arrangement did not increase the maximum thrust augmentation above that which was obtained using uniform primary nozzle injection angles. Diffuser blowing or suction did not provide an improvement in the maximum thrust augmentation above that which was obtained without diffuser boundary layer control. Finally, at low primary nozzle exit velocities, thrust augmentation increase as the nozzles were moved out along the inlet surface. The increase in thrust augmentation is attributed to the ability of the flow to remain attached to the inlet surface at low primary nozzle exit velocities thereby increasing the ejector effective mixing chamber length. (Author)
Experimental Investigation of a Circular Thrust Augmenting Ejector
1985
115 pages
Report
No indication
English
Jet & Gas Turbine Engines , Aircraft , Diffusers , Ejectors , Circular , Thrust , Angles , Injection , Inlets , Surfaces , Nozzles , Boundary layer control , Cross flow , Chambers , Length , Mixing , Height , Mass flow , Theses , Vertical takeoff aircraft , Entrainment , Thrust augmentation , Ratios
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