High-strength creep-resistant high-temperature alloy and preparation method thereof

A high-temperature alloy and anti-creep technology, which is applied in the field of metallurgy, can solve problems such as difficult to meet the technical requirements of aviation turboshaft engines, and achieve the effect of improving solid solution strengthening effect, temperature bearing capacity and strength level

Inactive Publication Date: 2022-07-12
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

However, the alloys in the prior art are difficult to meet the technical requirements of aviation turboshaft engines

Method used

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  • High-strength creep-resistant high-temperature alloy and preparation method thereof
  • High-strength creep-resistant high-temperature alloy and preparation method thereof
  • High-strength creep-resistant high-temperature alloy and preparation method thereof

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Embodiment Construction

[0040] In view of this, the present invention provides a high-strength creep-resistant superalloy and a preparation method thereof. The high-strength creep-resistant superalloy prepared by the preparation method can meet the requirements of future aviation turboshaft engines for high temperature resistance, high strength and creep resistance. The demand for variable performance is thus more suitable for practical use.

[0041] In order to further illustrate the technical means and effects adopted by the present invention to achieve the predetermined purpose of the invention, in conjunction with the accompanying drawings and preferred embodiments, a high-strength creep-resistant superalloy and a preparation method thereof proposed according to the present invention are described below. Embodiments, structures, features and their effects are described in detail as follows. In the following description, different "an embodiment" or "embodiments" do not necessarily refer to the sa...

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Abstract

The invention provides a high-strength creep-resistant high-temperature alloy and a preparation method thereof, and belongs to the technical field of metallurgy. The alloy comprises the following components in percentage by mass: 10.00%-12.00% of Cr, 12.00%-18.00% of Co, 5.50%-7.50% of W, 1.50%-3.50% of Mo, 3.00%-4.20% of Al, 3.00%-4.20% of Ti, 1.00%-2.20% of Nb, 0.40%-1.50% of Ta, 0.01%-0.04% of C, 0.01%-0.04% of B, 0.09%-1.20% of Zr, less than 0.10% of Hf and the balance of Ni, and the total mass percentage of gamma'phase forming elements Al, Ti, Nb and Ta in the high-temperature alloy is as follows: 9.5% < = (Al + Ti + Nb + Ta) < = 10.3%; the mass percentage content of a gamma'phase in the high-temperature alloy is 50%-55%, and the mass ratio of Al to Ti in the high-temperature alloy is that (Al/Ti) is larger than or equal to 0.9 and smaller than or equal to 1.0. The alloy and the disc piece of the alloy can be manufactured through the method, and the disc piece of the alloy can meet the requirements of future aviation turboshaft engines for high temperature resistance, high strength and creep resistance.

Description

technical field [0001] The invention relates to the technical field of metallurgy, in particular to a high-strength creep-resistant superalloy and a preparation method thereof. Background technique [0002] The powder pan is one of the most critical and core hot-end components of an aero-engine. The gradual improvement of engine performance requires turbine disk materials to have good comprehensive mechanical properties. Due to the advantages of uniform structure, fine grain size, high yield strength and good fatigue performance, powder superalloys have been successfully applied in many high-performance engines. However, it is difficult for the alloys in the prior art to meet the technical requirements of aeronautical turboshaft engines. SUMMARY OF THE INVENTION [0003] In view of this, the present invention provides a high-strength creep-resistant superalloy and a preparation method thereof. The high-strength creep-resistant superalloy prepared by the preparation metho...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C19/05C22F1/10B21J5/00C22B9/04C22C1/02C22C1/04
CPCC22C19/056C22C1/023C22C1/0433C22B9/04C22F1/10B21J5/002Y02T50/60
Inventor 彭子超王旭青汤悦罗学军刘健徐欢马国君
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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