Accession Number:

AD0831198

Title:

ADVANCED COMPOSITE CARBIDE NOZZLES.

Personal Author(s):

Corporate Author:

AEROJET-GENERAL CORP SACRAMENTO CA

Report Date:

1968-04-01

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

Descriptive Note:

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

Pages:

0111

Communities Of Interest:

Contract Number:

AF 04(611)-11608

File Size:

0.00MB

Full text not available:

Request assistance