Staged Combustion Rocket Motor for Storable Propellants.
Abstract
The combustion characteristics of a staged combustion rocket motor configuration were experimentally investigated. The motor consisted of a gas generator section and a secondary combustor with a conventional converging-diverging nozzle. The operation of the two chambers was effectively decoupled by means of a nozzle insert separating the two chambers designed such that the oxidizer rich gases generated were sonic at the entrance to the secondary chamber. The gas generator was operated over a range of mixture ratio from 10 to 20, o/F at chamber pressures from 600 to 1200 psia. The calculated cumbustion efficiencies ranged from 92% to 105% and stable operation was observed for all runs. No trends between combustion efficiency and the above parameters were observed. Various methods of injecting secondary liquid fuel into the sonic oxidizer rich gases were investigated. Existing correlations for penetration depth of a liquid jet injected into a gas stream were employed to isolate the dominant geometric and dynamic parameters. Ten impinging jet type injectors were experimentally evaluated over a range of fuel flow rates. The calculated combustion efficiencies ranged from 35% to 96% with the highest efficiencies calculated for the simplest geometric configurations. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1970
- Accession Number
- AD0867315
Entities
People
- C. F. Warner
- H. L. Dyer
Organizations
- Purdue University