EVALUATION OF AN ADVANCED NON-REGENERATIVELY COOLED ROCKET THRUST CHAMBER CONCEPT
Abstract
Subscale (100-lb) and fullscale (5000-lb) rocket thrust chambers of an advanced nonregeneratively cooled concept were designed, fabricated, and tested for durability at 500 psi chamber pressure, using N2O4/0.5 N2H4-0.5 UDMH propellants. The concept employs a silicon carbide-coated graphite thrust- chamber liner prestressed in compression by a refractory metal outer shell. The subscale units were successfully tested for continuous and intermittent firing durations exceeding 600 seconds. In the subscale tests, the inner SiC coatings were cracked through the nozzle region, but did not oxidize or erode. In both fullscale rocket thrust-chamber tests, the SiC coating fractured catastrophically during a 5-second test, leaving the graphite substrate unprotected. Test results and failure analyses indicate that a practical size/ configuration limit was exceeded for this structural design concept in progressing from the 1.75-inch diameter chambers to the 6.0-inch diameter chambers. Since the silicon-carbide coating is highly efficient from the environmental resistance aspect, new design concepts should be developed to circumvent the critcal size limitation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1967
- Accession Number
- AD0380951
Entities
People
- Ronald J. Taylor