Showing papers on "Metal matrix composite published in 1980"
TL;DR: In this article, the y-y'-Cr3C2 matrix composite material has been shown to have superior creep properties to current advanced superalloys at high temperatures (over 950 °C) but is subject to severe surface degradation in cyclic oxidation conditions by the spallation of chromium-rich oxide scales and by internal oxidation
Abstract: Metal matrix composite materials produced by the directional solidification of eutectic alloys continue to be advocated as future turbine blade materials. However, although considerable improvements in creep performance have been obtained from some eutectic alloys, relative to current superalloys, their oxidation and corrosion resistances have failed to meet the requirements for engine applications. One such alloy, designated y-y'-Cr3C2, consisting of a nickel matrix reinforced by cubic y' precipitate particles and aligned Cr3C2 fibres has been shown previously to have superior creep properties to current advanced superalloys at high temperatures (over 950 °C). However, the alloy is subject to severe surface degradation in cyclic oxidation conditions by the spallation of chromium-rich oxide scales and by internal oxidation
6 citations
TL;DR: In this paper, a technique has been developed with which to measure the radial strength of large diameter elastic fibres and it has been applied to the boron family of fibres.
6 citations
01 Jun 1980
TL;DR: In this paper, the relative manufacturing costs for large high technology fan blades prepared by advanced composite fabrication methods using seven candidate materials/process systems were estimated using analytical process models and all cost data are presented as normalized relative values where 100 was the cost of a conventionally forged solid titanium fan blade whose geometry corresponds to a size typical of 42 blades per disc.
Abstract: The relative manufacturing costs were estimated for large high technology fan blades prepared by advanced composite fabrication methods using seven candidate materials/process systems. These systems were identified as laminated resin matrix composite, filament wound resin matrix composite, superhybrid solid laminate, superhybrid spar/shell, metal matrix composite, metal matrix composite with a spar and shell, and hollow titanium. The costs were calculated utilizing analytical process models and all cost data are presented as normalized relative values where 100 was the cost of a conventionally forged solid titanium fan blade whose geometry corresponded to a size typical of 42 blades per disc. Four costs were calculated for each of the seven candidate systems to relate the variation of cost on blade size. Geometries typical of blade designs at 24, 30, 36 and 42 blades per disc were used. The impact of individual process yield factors on costs was also assessed as well as effects of process parameters, raw materials, labor rates and consumable items.
1 citations