Showing papers on "Metal matrix composite published in 1971"

Metal Matrix Composite Technology

Abstract: : The primary emphasis of the report pertains to the metal matrix composite system aluminum plus boron fiber with a protective coating. Alloys and fibers have been considered which are deemed most useful for aerospace applications. Further research and development will concentrate on composite systems for higher temperature application. It was found that, although environmental attack by salt water could be characterized by the matrix properties, degradation of properties at high temperatures in air (700C) were better related to the fibers. The transverse strength of boron-aluminum was related for the most part to the problem of fiber splitting and such effects as matrix, heat treatment, volume fraction fiber, test temperature, test specimen configuration, fiber properties, and secondary reinforcement were studied. Axial, transverse, and cross-ply composites were studied in low-cycle fatigue tests. Charpy 'V' notch bend tests and center-notched tensile tests were investigated to determine the effect of stress concentration factors and general fracture behavior. (Author)

Thermophysiochemical Compatibility between Metal Carbides and Metal Matrices.

Abstract: : A method of fabricating carbide-metal interaction specimens was developed and is described. The diffusion bonded specimens were employed in the experimental evaluation of the compatibility of MC type carbides in high temperature metal matrices. This was accomplished in an effort to evaluate the stability of the MC type carbide in terms of its potential use as a diffusion barrier in a carbon filament reinforced high temperature metal matrix composite system. Six MC type carbides were chosen based on structural and thermodynamics consideration. These carbides were: TiC, VC, HfC, TaC, NbC, and ZrC and were evaluated in pure Ni, pure Co, Ni-20Cr, Co-19.5Cr, IN 100, and MAR-M-509. The diffusion couples were evaluated after 25 hours at temperatures from 1000 to 1200C. (Author)

Metal Matrix Composite Fabrication Procedures for Gas Turbine Engine Blades

Abstract: Metal matrix composites constitute an attractive class of materials which must be considered as serious candidates for application in advanced gas turbine engines. Materials development programs have been successful in fabricating and characterizing metallic composite materials. Demonstration programs have shown that aerospace structural components can be fabricated from them. This paper deals with the application of the diffusion bonding process to the formation of a complex shape such as a gas turbine engine fan blade from titanium or aluminum matrix composites. It deals with the route to volume producibility rather than with the documentation of progress to date.Copyright © 1971 by ASME