Accession Number : AD0843593
Title : Demonstration of a Submerged Cooled Nozzle.
Descriptive Note : Final program rept., 1 Oct 65-15 Nov 68,
Corporate Author : AEROJET-GENERAL CORP SACRAMENTO CA
Personal Author(s) : Baker, W. H., Jr
Report Date : NOV 1968
Pagination or Media Count : 378
Abstract : The feasibility of evaporatively cooling refractory throat liners with boiling lithium was demonstrated by test firing a refractory throat liner at 670 psia and 6500F for 60 sec with no erosion. It was determined that throat sizes could be increased approximately 20% by reinforcement rings welded to the coolant side of the throat liner and this design feature was demonstrated in a nozzle test firing. In addition to verification of the lithium pool boiling concept, the test firing verified thermal and stress analyses of complex shapes using tantalum-tungsten T-222. During this program, this material was fully characterized in terms of elevated temperature mechanical and physical properties of both parent and welded material. Spinning and welding procedures were established for forming high quality nozzle components from T-222 and C-103 components. (Author)
Descriptors : (*ROCKET NOZZLES, COOLING), LIQUID METAL COOLANTS, LITHIUM, EVAPORATION, FEASIBILITY STUDIES, NOZZLE THROATS, REFRACTORY MATERIALS, TANTALUM ALLOYS, TUNGSTEN ALLOYS, NIOBIUM ALLOYS, EROSION, HEAT TRANSFER, THERMAL STRESSES, METAL SPINNING, WELDING, SOLID PROPELLANT ROCKET ENGINES.
Subject Categories : Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE