Accession Number : AD0827451
Title : REFRACTORY TUBE TEST CHAMBER AND MATERIALS EVALUATION PROGRAM.
Descriptive Note : Final rept. Jul 65-Aug 67,
Corporate Author : ROCKETDYNE CANOGA PARK CA
Personal Author(s) : Greenfield, S. ; Chandler, W. T. ; Nagai, C. ; Meerbaum, S. ; Hensley, W. E.
Report Date : JAN 1968
Pagination or Media Count : 336
Abstract : The objectives of the program were to develop a test apparatus capable of rapidly and economically evaluating refractory metal tubes under rocket thrust chamber environments, and to evaluate selected refractory metals in tube form with the test apparatus. The program was divided into two phases. Phase I provided a design, fabrication, and test checkout of a test thrust chamber under conditions of chamber pressure and mixture ratio which provided peak heat fluxes approaching 50 Btu/sq. in.-sec for a minimum of 20 seconds. Phase II consisted of an experimental evaluation of selected refractory metals, in tube form, over a range of chamber pressures and mixture ratios typical of rocket engine operation, using the propellant combination N2O4/N2H4-UDMH(50-50). Nine refractory alloys were tested, representing columbium, tantalum, tungsten, and molybdenum classes of materials. (Author)
Descriptors : (*ROCKET COMPONENTS, REFRACTORY MATERIALS), (*REFRACTORY METAL ALLOYS, TEST FACILITIES), LIQUID PROPELLANT ROCKET ENGINES, COMBUSTION CHAMBERS, ROCKET NOZZLES, REGENERATIVE COOLING, PIPES, INJECTORS, NOZZLE INSERTS, NIOBIUM ALLOYS, TANTALUM ALLOYS, TUNGSTEN ALLOYS, MOLYBDENUM ALLOYS, RHENIUM ALLOYS, REFRACTORY COATINGS.
Subject Categories : Metallurgy and Metallography
Test Facilities, Equipment and Methods
Distribution Statement : APPROVED FOR PUBLIC RELEASE