Accession Number:

AD0831198

Title:

ADVANCED COMPOSITE CARBIDE NOZZLES.

Descriptive Note:

Interim progress rept. 1 Jul 67-29 Mar 68,

Corporate Author:

AEROJET-GENERAL CORP SACRAMENTO CA

Personal Author(s):

Report Date:

1968-04-01

Pagination or Media Count:

111.0

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 microcomposite of monocarbide tantalum and hafnium and a tantalum-carbide-coated, tantalum carbidegraphite hypereutectic. During this reporting period, the characterization of ambient and elevated temperature properties has been completed on both the microcomposite and TaC-C hypereutectic composite systems. Thermal shock resistance and chemical corrosion evaluation tests have been completed on both composite systems. Testing was conducted in a hyperthermal environmental simulator using subscale inserts. The fusion casting of 4.2-in.-dia TaC-C hypereutectic billets are presently in progress for fabricating full-scale nozzle inserts. Author

Subject Categories:

  • Laminates and Composite Materials
  • Properties of Metals and Alloys
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE