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

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

Subject Categories:

  • Properties of Metals and Alloys
  • Combustion and Ignition
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE