Accession Number:

AD0384477

Title:

ADVANCED PROPELLANT STAGED-COMBUSTION FEASIBILITY PROGRAM

Descriptive Note:

Final rept. Dec 1965-Jul 1967 on Phase 2

Corporate Author:

AEROJET-GENERAL CORP SACRAMENTO CA LIQUID ROCKET DIV

Personal Author(s):

Report Date:

1967-09-01

Pagination or Media Count:

312.0

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 H2O2Alumizine-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 H2O2Alumizine-43 propellant combination.

Subject Categories:

  • Liquid Propellant Rocket Engines
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE