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) : Radtke, R. P. ; Swope, L. M.

Report Date : APR 1968

Pagination or Media Count : 111

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 carbide/graphite 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)

Descriptors :   *NOZZLE INSERTS), (*ROCKET NOZZLES, (*CARBIDES, COMPOSITE MATERIALS), HIGH TEMPERATURE, EXHAUST FLAMES, TANTALUM, HAFNIUM, GRAPHITE, EUTECTICS, CASTING, PHASE STUDIES, THERMAL PROPERTIES, TEST METHODS, FLEXURAL STRENGTH, PRESSURE, CORROSION, THERMAL STRESSES, SHOCK RESISTANCE.

Subject Categories : Laminates and Composite Materials
      Properties of Metals and Alloys
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE