ADVANCED PROPELLANT STAGED-COMBUSTION FEASIBILITY PROGRAM
Abstract
The major objective of this program was the definition of problems associated with the use of 98 percent hydrogen peroxide (H2O2) and Alumizine-43 in a staged-combustion rocket engine system. In the cooled version of the engine conceived, all of the H2O2 is used to regeneratively cool a secondary combustor (in which Alumizine-43 is burned) before the H2O2 passes through the preburner catalyst pack and the turbine. Phase II research consisted of a series of 20,000-lbf preburner and staged-combustion evaluation tests. The Phase II technical achievements included the completion of a H2O2 experimental heat-transfer program, a preburner test program, and a staged-combustion test program. Satisfactory operation of a 98 percent H2O2 preburner was demonstrated at throughputs from 48 to 108.2 psim for two catalyst configurations. Staged combustion at 3000 psia with 98 percent H2O2/Alumizine-43 was demonstrated satisfactorily with two secondary injector concepts. Heat-transfer data on critical areas of the chamber and throat were obtained. The experimental performance of the propellant combination was determined over a range of mixture ratios with two different L* chambers. The performance of 90 percent H2O2/ Alumizine-43 was determined and compared to the 98 percent H2O2/Alumizine-43 propellant combination.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1967
- Accession Number
- AD0384477
Entities
People
- Robert J. Kuntz
- Roy G. Sjogren
Organizations
- Aerojet Rocketdyne Holdings