Accession Number : AD0438815


Title :   RESEARCH AND DEVELOPMENT OF TITANIUM ROCKET MOTOR CASE. VOLUME I. FORGING OF FRONT AND REAR CLOSURES.


Descriptive Note : Final technical rept., 30 June 60-30 Sep 63,


Corporate Author : PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN


Personal Author(s) : Godfrey,L ; Makowski,R


Report Date : 31 Oct 1963


Pagination or Media Count : 271


Abstract : Subscale and full scale rocket motor case closures were forged to develop economical fabrication techniques which would produce forgings with consistently high strength levels. Forgings were intended to meet a design requirement of a 180,000 psi minimum yield strength level with 4% minimum elongation. Initial evaluation of the effects of oxygen indicated that contents between 0.11 and 0.17 weight per cent were acceptable. Evaluation of full scale forgings indicated, however, that parts with oxygen contents below 0.12% were not capable of attaining the 180,000 to 200,000 psi yield strength level throughout with adequate ductility, and therefore it is recommended that forgings of B-120 VCA titanium alloy contain a minimum of 0.12, a maximum of 0.17, and a nominal 0.14 weight per cent oxygen. The maximum value was established on the basis of ductility deterioration. (Author)


Descriptors :   TITANIUM ALLOYS , ROCKET ENGINE CASES , FORGING , ALUMINUM ALLOYS , CHROMIUM ALLOYS , VANADIUM ALLOYS , HEAT TREATMENT , DUCTILITY , OXYGEN , RUPTURE , MATERIAL FORMING , GRAIN STRUCTURES(METALLURGY)


Distribution Statement : APPROVED FOR PUBLIC RELEASE