Air Augmented Rocket Fixed Fuel Flow Combustion Characterization Program.
Abstract
This program demonstrated that reliable, consistent combustion efficiency data could be obtained independently at different facilities. The detailed combustion efficiency performance of two Boron loaded fuel rich propellants was mapped over an air-to-fuel ratio range from 10 to 40 and a ramburner air-only pressure range from 13 to 40 psia. Two highly loaded Boron propellants were used. Testing was conducted at three facilities. Six inch subscale hardware was utilized and a coaxial mixing configuration chosen. Data analysis procedures were refined and error sources (particularly fuel flow rate uncertainties) minimized. The averaged combustion efficiency data from all three facilities fell within the computed error bands, + or - 5.5 percent. Significant A/F dependence was found for combustion efficiency for the two propellants. The effect of fuel generator pressure on combustion efficiency was briefly investigated and found to be negligible. Finally, a propellant comparison was made and ARC 256A had generally better combustion efficiency performance and a higher theoretical heating value, leading to its selection as the superior propellant. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1973
- Accession Number
- AD0525525
Entities
People
- Jerry L. Fields