Accession Number : AD0834003

Title :   INVESTIGATION OF COMBUSTION CHARACTERISTICS OF A BI-PHASE ROCKET,

Corporate Author : PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER

Personal Author(s) : Netzer, D. W. ; Osborn, J. R.

Report Date : APR 1968

Pagination or Media Count : 203

Abstract : An investigation was conducted (a) to test the ability of the Priem-Heidmann propellant vaporization model to predict the steady-state operating characteristics of a bi-phase rocket motor, (b) to determine the validity of the vaporization limited Priem-Guentert non-linear instability model for predicting the magnitude of a pressure disturbance required to initiate combustion instability, and (c) to determine the applicability of the Feiler-Heidmann response factor model to bi-phase propellant systems. The investigation employed bi-phase propellants (either normal pentane or normal heptane as the fuel and air as the oxidizer) injected into the chamber through co-axial injector elements. Results of the investigation indicated the existence of a 'stability drop size' above which practically all tests were extremely stable and below which the vast majority of tests were spontaneously unstable. The degree of instability increased substantially as the mass mean drop size was decreased. The fuel flow rate and contraction ratio affected the stability although to a lesser degree than the drop size; the degree of instability decreased with increasing contraction ratio and decreasing fuel mass flow rate. (Author)

Descriptors :   (*LIQUID PROPELLANT ROCKET ENGINES, COMBUSTION), (*COMBUSTION, STABILITY), COMBUSTION, LIQUID ROCKET FUELS, AIR, VAPORIZATION, DROPS, MATHEMATICAL MODELS, PREDICTIONS, MODEL TESTS, FUEL INJECTORS, PRESSURE, THERMAL ANALYSIS, MATHEMATICAL PREDICTION.

Subject Categories : Combustion and Ignition
      Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE