An Investigation of the Static Thrust Augmentation Capabilities of a Divergent Ejector-Afterburner
AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING
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The effects on static thrust augmentation and mass entrainment of various divergent ejector-afterburner configurations were investigated. Static tests were conducted using a gaseous oxygenhydrogen sonic rocket as the primary gas generator. Configurations included various length mixing ducts, two different size diffusers, burn ducts, and secondary nozzles. Oxydizer-to-fuel mixture ratio was varied from .3 to 1.5 at 80 psia chamber pressure. Results indicated maximum static thrust augmentation 220 when the relatively unmixed primary and secondary streams were diffused immediately after the secondary inlet and then allowed to complete mixing in a constant area duct, for a total afterburner length of about six inlet diameters.
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