AN INVESTIGATION OF THE EFFECTS OF SECONDARY STREAM TURBULATION ON THE THRUST AUGMENTATION OF AN EJECTOR-AFTERBURNER

Secondary stream turbulation of a supersonic ejector-afterburner was investigated using a nominal 65 pounds thrust gaseous hydrogen-oxygen rocket engine. The afterburner had a length-to-diameter ratio of 9 and an afterburner exit to nozzle-exit area ratio of 5.1. Several turbulator configurations, w...

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Bibliographische Detailangaben
1. Verfasser:	Adam, Wallace B
Format:	Report
Sprache:	eng
Schlagworte:	AFTERBURNERS Fluid Mechanics HYDROGEN Jet and Gas Turbine Engines JET MIXING FLOW LIFT-DRAG RATIO Liquid Propellant Rocket Engines OXYGEN PERFORMANCE(ENGINEERING) ROCKET NOZZLES SECONDARY FLOW SPECIFIC IMPULSE SUPERSONIC CHARACTERISTICS THESES THRUST AUGMENTATION TURBULENCE
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Zusammenfassung:	Secondary stream turbulation of a supersonic ejector-afterburner was investigated using a nominal 65 pounds thrust gaseous hydrogen-oxygen rocket engine. The afterburner had a length-to-diameter ratio of 9 and an afterburner exit to nozzle-exit area ratio of 5.1. Several turbulator configurations, with aerodynamic blockage ratios from 0.123 to 0.516, were tested at three locations relative to the secondary stream inlet. Results showed that at mixture ratios less than 0.8, the performance of the ejector-afterburner could be improved with secondary stream turbulation. (Author)