Engineering Papers⌕ Search

Engineering topics

Weeton, J. W.

Publications and source records attributed to Weeton, J. W..

At least 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1981

Method for alleviating thermal stress damage in laminates

The method is for metallic matrix composites, such as laminated sheet or foil composites. Non-intersecting discrete discontinuities are positively introduced into the interface between the layers so as to reduce the thermal stress produced by unequal expansion of the materials making up the composite. The discontinuities are preferably produced by drilling holes in the metallic matrix layer. However, a plurality of discrete elements may be used between the layers to carry out this purpose.

Hoffman, C. A.↗
NASA NTRS1980

Method for alleviating thermal stress damage in laminates

A method is provided for alleviating the stress damage in metallic matrix composites, such as laminated sheet or foil composites. Discontinuities are positively introduced into the interface between the layers so as to reduce the thermal stress produced by unequal expansion of the materials making up the composite. Although a number of discrete elements could be used to form one of the layers and thus carry out this purpose, the discontinuities are preferably produced by simply drilling holes in the metallic matrix layer or by forming grooves in a grid pattern in this layer.

Hoffman, C. A.↗
NASA NTRS1974

A study of stress-rupture and ductility properties of thin laminae composites

It is shown that, by rolling, tungsten-tantalum laminar composites can be reduced in thickness as much as 90 to 1, with a resulting improvement in strength of nearly 66%. Further reductions in laminar thickness are believed to be possible with further increases in the strength of the composite material. The rolled tungsten-tantalum laminar material shows also a remarkable low-temperature ductility, sustaining a 3-T bend at room temperature without incurring macrodamage.

Hoffman, C. A.↗
NASA NTRS1973

Metal-metal reinforced laminar composites

Two prototype laminar composites have shown potential for high strength and high temperature applications. These composites might be made with less in-place anisotropy and be less expensive than comparable fiber composites.

Weeton, J. W.↗
NASA NTRS1973

Metal-metal laminar composites for high-temperature applications.

A study was conducted to obtain indications of the potentialities of laminar metal-metal composites for elevated-temperature use. Most of the composites consisted of multiple layers or laminae of tungsten alternated with laminae of Nichrome V, a ductile, weaker, but oxidation-resistant alloy. Composites with 50 vol % of each phase made from 0.0025 cm, 0.0125 cm, or 0.050 cm laminae, were tested in tension and stress rupture at temperatures of 871 and 1093 C and in impact at 23 and 524 C. A tension and a short-time stress-rupture test was conducted on specimens of 77 vol % W-Re-Hf-C/23 vol % Inconel Alloy 600 at 1093 C.

Hoffman, C. A.↗
NASA NTRS1972

Metal-metal laminar composites for high-temperature applications.

The potentialities of composites consisting of multiple layers of tungsten alternated by layers of Nichrome V (a ductile, weaker than tungsten, but oxidation resistant alloy) at temperatures on the order of 2000 F are studied experimentally. The highest tensile strengths obtained for the composites were 600 MN/sq m (87,000 psi) at 1600 F and 448 MN/sq m (65,000 psi) at 2000 F. Highest 100-hr stress-rupture strengths at these temperatures were 387 MN/sq m (56,000 psi) and 121 MN/sq m (17,500 psi), respectively.

Hoffman, C. A.↗
NASA NTRS1972

Metal-metal laminar composites for high temperature applications

A study was conducted to obtain indications of the potentialities of laminar metal-metal composites for elevated temperature use. Most of the composites consisted of multiple layers or laminae of tungsten alternated with laminae of Nichrome V, a ductile, weaker but oxidation-resistant alloy. Composites with 50 volume percent of each phase were tested in tension and stress rupture at temperatures of 871 and 1093 C (1600 and 2000 F) and in impact at 23 and 524 C (73 and 975 F). A tension and a short time stress-rupture test was conducted on specimens of 77 v/o W-Re-Hf-C/23 v/o Inconel alloy 600 at 1093 C (2000 F).

Hoffman, C. A.↗