Manufacturing method of iron-based high-temperature alloy for aerospace fastener

The invention provides a manufacturing method of an iron-based high-temperature alloy for an aerospace fastener. The manufacturing method is characterized by comprising the working procedures of vacuum induction (VIM), electroslag remelting (ESR), forging, nondestructive testing and rolling which ar...

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Bibliographische Detailangaben
Hauptverfasser:	XIA PANKE, WANG JING, LIU SHANGTAN, DING QI
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	ALLOYS CHEMISTRY FERROUS OR NON-FERROUS ALLOYS FORGE FURNACES FORGING GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUSMETALS OR ALLOYS HAMMERING MAKING METAL MALLEABLE BY DECARBURISATION, TEMPERING OR OTHERTREATMENTS MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVINGMATERIAL METALLURGY METALLURGY OF IRON MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS PERFORMING OPERATIONS PRESSING METAL PRETREATMENT OF RAW MATERIALS PROCESSING OF PIG-IRON, e.g. REFINING, MANUFACTURE OFWROUGHT-IRON OR STEEL PRODUCTION AND REFINING OF METALS PUNCHING METAL RIVETING ROLLING OF METAL TRANSPORTING TREATMENT IN MOLTEN STATE OF FERROUS ALLOYS TREATMENT OF ALLOYS OR NON-FERROUS METALS
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Beschreibung
Zusammenfassung:	The invention provides a manufacturing method of an iron-based high-temperature alloy for an aerospace fastener. The manufacturing method is characterized by comprising the working procedures of vacuum induction (VIM), electroslag remelting (ESR), forging, nondestructive testing and rolling which are carried out in sequence. Wherein the vacuum induction VIM means that the melting process and the refining process are controlled to be carried out under the high-vacuum condition with the vacuum degree smaller than 2.0 Pa; a slag system of the electroslag remelting ESR adopts quaternary pre-melting slag; the quaternary pre-melting slag is prepared from CaF2, Al2O3, CaO and MgO; the heating temperature of forging is not higher than 1200 DEG C; the rolling heating temperature is not higher than 1200 DEG C. The alloy is stable in structure, the size change and fastening force of a fastener are reduced, and the service life is long. 本发明提供了一种航空航天紧固件用铁基高温合金的制造方法，其特征在于：包含顺序进行的真空感应VIM、电渣重熔ESR、锻造、无损检测和轧制工序；其中，所述真空感应VIM指控制