Accession Number : AD0507622

Title :   Development and Demonstration of Passively Cooled Thrust Chamber Assemblies for Fluorinated Propellants.

Descriptive Note : Interim rept. 15 Feb 68-Jan 70 on Phase 1,

Corporate Author : AEROJET-GENERAL CORP SACRAMENTO CALIF LIQUID ROCKET DIV

Personal Author(s) : Dickson,James C. ; Schindler,Robert C.

Report Date : FEB 1970

Pagination or Media Count : 120

Abstract : This study was a two-phase development program which evaluated 3000-lb thrust (sea level), passively cooled thrust chambers at chamber pressures of 300 and 500 psia using fluorinated oxidizer and amine fuels. Phase I was a 17-month effort consisting of the design, fabrication, test, and posttest analysis of two thermally instrumented thrust chambers. These were each tested at 300 psia chamber pressure and accumulated 400 sec of operation on a duty cycle that included multiple hot and cold restarts and long-duration firings with two types of propellants: ClF/3 MMH and ClF3/BA-1014. Phase II was a 6-month effort consisting of the design, fabrication, and posttest analysis of one thermally instrumented thrust chamber which was operated at 500 psia chamber pressure using ClF3/M-20 propellant.

Descriptors :   (*COMBUSTION CHAMBERS, COOLING), (*LIQUID ROCKET PROPELLANTS, FLUORINATION), THRUST, PASSIVE SYSTEMS, COMPOSITE MATERIALS, LIQUID PROPELLANT ROCKET ENGINES, ABLATION, COMBUSTION CHAMBER LINERS, DEPOSITION (U) CHLORINE COMPOUNDS, FLUORIDES, ROCKET NOZZLES, GRAPHITE, PRESSURE, HYDRAZINE, LIQUID ROCKET OXIDIZERS, AMINES, METHYL HYDRAZINES, CARBON FIBERS, NOZZLE THROATS, FUEL INJECTORS, PHENOLIC PLASTICS, REINFORCING MATERIALS, COMBUSTION CHAMBER GASES, THERMAL INSULATION

Subject Categories : Rocket Engines
      Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE