Preparation method of powder high-temperature alloy component containing inclusions

By simulating and preparing the sheath unit through simulation software, the position and size of inclusions in the powder high-temperature alloy components are controlled, which solves the problem of uncontrollable inclusions in the existing technology, improves the simulation accuracy, and meets the airworthiness certification requirements.

CN120758757AActive Publication Date: 2025-10-10INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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Patent Information

Application Number
CN202511286175.8
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-09-10
Publication Date
2025-10-10
Estimated Expiration
2045-09-10

AI Technical Summary

Technical Problem

Existing technologies are unable to effectively control the number, location, and distribution of inclusions in powder high-temperature alloy components, resulting in poor accuracy in simulating real components and failing to meet airworthiness certification requirements.

Method used

The implantation position and size of inclusions are simulated using simulation software. By preparing the jacket unit, vacuum sintering and hot isostatic pressing, the type, size and position of the inclusions are controlled to produce powder high-temperature alloy components containing inclusions.

Benefits of technology

It achieves precise control of inclusions, improves the accuracy of simulating real components, reduces errors, and provides technical support for airworthiness certification research.

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Abstract

The invention relates to a preparation method of a powder high-temperature alloy component containing inclusions, and relates to the technical field of powder metallurgy and the technical field of airworthiness certification and evaluation of aero-engines. The preparation method comprises the following steps: preparing a sheath for powder metallurgy forming based on the size of a required powder high-temperature alloy component, and cutting the sheath into a plurality of parts to obtain a plurality of sheath units; the inclusion implantation position is located at the segmentation position of the sheath; high-temperature alloy powder is loaded into each sheath unit, and then vacuum sintering treatment is carried out, so that the high-temperature alloy powder in each sheath unit is solidified into a high-temperature alloy part; the multiple high-temperature alloy components are combined, and a powder high-temperature alloy combined part is obtained; in the combination process, the inclusion needs to be implanted in the inclusion implantation position; and the powder high-temperature alloy assembly is subjected to hot isostatic pressing treatment, and the powder high-temperature alloy component containing the inclusions is obtained. The method is used for improving the accuracy of simulating real components so as to meet the urgent demand of airworthiness certification.
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