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DETERMINATIONS OF LOCAL AND INSTANTANEOUS COMBUSTION CONDITIONS FROM ACOUSTIC MEASUREMENTS IN A ROCKET COMBUSTOR AND COMPARISON WITH OVER-ALL PERFORMANCE
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C
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Simultaneous local and instantaneous combustion conditions, over-all characteristic exhaust velocity efficiencies, and local chamber efficiencies were determined for a 100-lb thrust gaseous H2 combustor burning either gaseous or liquid O2 over an oxidant-fuel ratio of range of 3.2 to 10.0 at a chamber pressure of 200 lbsq in. Combustion conditions were determined from measurements of the sound velocity at a single station in the chamber. Combustor performance varied with of from about 80 to 100 percent of theoretical for liquid O2 and was about 92 percent and independent of of for gaseous O2. The results of sound velocity measurements indicated the presence of random fluctuations of composition and temperature of the combustion gases. Losses in performance may therefore have been due to poor mixing and random burning fluctuations. Author
APPROVED FOR PUBLIC RELEASE