INVESTIGATION OF COMBUSTION CHARACTERISTICS OF A BI-PHASE ROCKET,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1968
- Accession Number
- AD0834003
Entities
People
- D. W. Netzer
- J .r. Osborn
Organizations
- Purdue University