Accession Number:
AD0817208
Title:
ADVANCED COMPOSITE CARBIDE NOZZLES.
Descriptive Note:
Interim progress rept. 1 Jan-30 Jun 67,
Corporate Author:
AEROJET-GENERAL CORP SACRAMENTO CA
Personal Author(s):
Report Date:
1967-07-01
Pagination or Media Count:
85.0
Abstract:
The purpose of this program is to develop two thermal-shock-resistant composite carbide systems that can be reliably used with high-flame-temperature solid rocket propellants. These are a micro-composite of monocarbide tantalum, hafnium and a tantalum-carbide-coated, tantalum carbidegraphite hypereutectic. During the report period, ambient-temperature physical-property screening tests have been completed on six candidate micro-composite compositions. Elevated temperature mechanical and thermal property testing has been partly completed on one of the two micro-composite compositions selected as a candidate rocket nozzle material. Scale-up has been initiated in a newly developed hot-press and fusion casting furnace facility for fabricating the tantalum carbidegraphite hypereutectic composites. Author
Descriptors:
- *ROCKET NOZZLES
- *EXHAUST FLAMES
- CARBIDES
- NOZZLE INSERTS
- HEAT RESISTANT ALLOYS
- SOLID PROPELLANT ROCKET ENGINES
- COMPOSITE MATERIALS
- THERMAL SHOCK
- SHOCK RESISTANCE
- HIGH TEMPERATURE
- REFRACTORY METAL ALLOYS
- HEAT RESISTANT MATERIALS
- EXHAUST GASES
- MANUFACTURING
- TANTALUM ALLOYS
- HAFNIUM ALLOYS
- GRAPHITE
- METAL COATINGS
- PHASE STUDIES
- EUTECTICS
- MODEL TESTS
- EROSION
- REFRACTORY COATINGS
- REFRACTORY COATINGS
Subject Categories:
- Properties of Metals and Alloys
- Combustion and Ignition
- Rocket Engines