SE359119

1,196,529. Carbide fibre containing alloys. UNITED AIRCRAFT CORP. Oct. 10, 1968 [Oct. 11, 1967], No. 47988/ 68. Heading C7A. [Also in Division B3] An article of manufacture, such as an anisotropic jet engine turbine component, comprises a composition of Ni, Co, or Cr, with a monocarbide of one of Ti...

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Bibliographische Detailangaben
Hauptverfasser:	LEMKEY F,US, THOMPSON E,US
Format:	Patent
Sprache:	eng
Schlagworte:	AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUSPOLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE ALLOYS APPARATUS THEREFOR CHEMISTRY CRYSTAL GROWTH FERROUS OR NON-FERROUS ALLOYS METALLURGY PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITHDEFINED STRUCTURE REFINING BY ZONE-MELTING OF MATERIAL SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITHDEFINED STRUCTURE SINGLE-CRYSTAL-GROWTH TREATMENT OF ALLOYS OR NON-FERROUS METALS UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL ORUNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL
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Beschreibung
Zusammenfassung:	1,196,529. Carbide fibre containing alloys. UNITED AIRCRAFT CORP. Oct. 10, 1968 [Oct. 11, 1967], No. 47988/ 68. Heading C7A. [Also in Division B3] An article of manufacture, such as an anisotropic jet engine turbine component, comprises a composition of Ni, Co, or Cr, with a monocarbide of one of Ti, Zr, Hf, V, Nb, or Ta at about the eutectic composition, the carbide component being present predominantly in the form of high strength fibres oriented in generally parallel spaced relationship, integrally imbedded in a matrix. The compositions are made by melting the starting materals in the inert atmosphere (e.g. in closed end alumina crucible with a water chill) at a rate sufficient to establish and maintain planar front solidification (e.g. with a velocity below 3cm/hr), the direction of solidification generally corresponding to the anticipated tensile load axis of the component.