A creep-resistant and heat-resistant titanium-based composite material and its preparation method

By optimizing the content of reinforcing phases and the composition of the matrix alloy, and combining vacuum consumable melting, slab forging and heat treatment processes, a creep-resistant and heat-resistant titanium-based composite material was prepared. This solved the problem of insufficient high-temperature creep performance of titanium-based composite materials and achieved a significant improvement in the matching of high-temperature creep resistance and strength-plasticity.

CN117821803BActive Publication Date: 2026-06-30AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
Filing Date
2024-01-03
Publication Date
2026-06-30

AI Technical Summary

Technical Problem

Existing titanium-based composite materials have insufficient overall performance matching in terms of high-temperature creep properties, especially with low creep performance under low stress conditions, which makes it difficult to meet the application requirements of aerospace and other fields.

Method used

By optimizing the content of reinforcing phase and the content of Al and Mo in the matrix alloy, a creep-resistant and heat-resistant titanium-based composite material was prepared by using vacuum arc remelting, slab forging, high-temperature hot rolling and heat treatment processes. The specific steps include vacuum arc remelting, slab forging, hot rolling and heat treatment to form a wide thin plate.

Benefits of technology

It improves the high-temperature creep resistance of the material, achieves a good match between high-temperature strength and plasticity, with creep residual strain of less than 0.2% at 650℃/100MPa/100h, significantly extended creep fracture time, and low cost.

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Abstract

This invention belongs to the field of titanium-based composite material technology, specifically relating to a creep-resistant heat-resistant titanium-based composite material and its preparation method. The method includes: vacuum arc remelting: preparing a heat-resistant titanium-based composite material ingot through three vacuum arc remelting processes; slab forging: forging the obtained ingot and preparing a slab; high-temperature hot rolling: hot rolling the forged composite material slab at high temperature to obtain a wide semi-finished thin plate; and heat treatment: performing vacuum heat treatment on the rolled heat-resistant titanium-based composite material plate to control its performance. By employing specific component ratios and processes, a wide thin plate is prepared through vacuum arc remelting, slab forging, high-temperature hot rolling, and heat treatment. Compared to existing technologies, this method results in a material with excellent high-temperature creep resistance, achieving comprehensive performance requirements of high strength, high ductility, low creep residual strain, and long creep rupture time, thus meeting the stringent requirements of the aerospace field for heat-resistant structural materials.
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