Development and Demonstration of Passively Cooled Thrust Chamber Assemblies for Fluorinated Propellants.
Abstract
This report is a two-phase development program to evaluate 300-lb thrust passively cooled thrust chambers at chamber pressures of 300 and 500 psi in a long-duration fluorinated oxidizer propellant environment. Phase I was a 17-month effort consisting of the design, fabrication, test and analysis of two thermally instrumented thrust chambers tested at 300-psi chamber pressure for over a 400-sec duty cycle that included multiple hot and cold restarts and long-duration tests with two types of propellants: CTF/MMH and CTF/BA-1014. Both thrust chambers used fibrous graphite (AGCarb-101) in the throat region and graphite phenolic ablative material in the upstream portion of the chamber. The first chamber design used a fibrous graphite throat insert which was mechanically restrained and insulated by a structural overwrap capable of withstanding high temperatures. The second chamber was identical in internal geometry to the first but but used the AGCarb-101 fibrous graphite material as a thin-wall self-supporting radiation member externally insulated by a nonload-carrying ablative shield. Post firing analysis indicated that AFRPL's like doublet multielement injector and both Phase I thrust chambers were capable of additional long-duration testing.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1969
- Accession Number
- AD0505451
Entities
People
- James C. Dickson
- Robert C. Schindler
Organizations
- Aerojet Rocketdyne Holdings