Accession Number : ADA303197
Title : Liquid Rocket Motor Combustion Stability Using Coaxial Injectors and Supercritical Droplet Combustion and Dynamics.
Descriptive Note : Final rept.,
Corporate Author : PENNSYLVANIA STATE UNIV UNIVERSITY PARK
Personal Author(s) : Micci, Michael M. ; Yang, Vigor
PDF Url : ADA303197
Report Date : MAY 1995
Pagination or Media Count : 222
Abstract : Cold flow experiments with a full-size SSME preburner shear coaxial injector element using liquid and gaseous nitrogen at pressures up to 4 MPa showed that the intact liquid core decreased in length with increasing chamber pressure up to the critical pressure, after which it increased in length. Increasing the liquid to gas mass flow rate ratio resulted in an increase in the length of the liquid core. LDV measurements showed flow recirculation downstream of the LOX post. Results from a linearized model of the injector, combustion and vaporization processes compared well to unsteady pressure measurements made during liquid oxygen/gaseous hydrogen hot-fire tests. Vaporization and combustion of liquid droplets in both subcritical and supercritical environments have been studied systematically. A variety of liquid propellants and propellant simulants, including hydrobon and cryogenic fluids, in both steady and oscillatory environments were treated numerically. Because the model allows solutions from first principles, a systematic examination of the droplet behavior over wide ranges of pressure, temperuture, and ambient flow velocity is made possible. Results can not only enhance the basic understanding of the problem, but can also serve as a basis for establishing droplet vaporization and combustion correlations for the study of liquid rocitet engine combustion, performance, and stability. (AN)
Descriptors : *LIQUID PROPELLANT ROCKET ENGINES, *COMBUSTION STABILITY, PRESSURE GRADIENTS, MATHEMATICAL MODELS, REACTION KINETICS, COMPUTATIONAL FLUID DYNAMICS, FLOW VISUALIZATION, PRESSURE MEASUREMENT, HYDROGEN, COAXIAL CONFIGURATIONS, CORRELATION, MASS FLOW, TEMPERATURE GRADIENTS, DROPS, COMBUSTION CHAMBERS, SUPERCRITICAL FLOW, UNSTEADY FLOW, LIQUID NITROGEN, INJECTORS, INSTABILITY, SPRAYS, TWO PHASE FLOW, GAS SURFACE INTERACTIONS, NOZZLE GAS FLOW, EQUATIONS OF STATE, DOWNSTREAM FLOW, VAPORIZATION, LASER VELOCIMETERS, AXIAL FLOW, STEADY FLOW, VARIABLE PRESSURE, LIQUID OXYGEN, RECIRCULATION, ATOMIZATION, CRYOGENIC PROPELLANTS, COLD FLOW.
Subject Categories : Combustion and Ignition
Liquid Propellant Rocket Engines
Liquid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE