High-temperature alloy with low stacking fault energy, structural part and application of high-temperature alloy

A technology of high-temperature alloys and structural parts, which is applied in the direction of supporting components of blades, engine components, machines/engines, etc., to achieve excellent process performance, improve process performance, and improve high-temperature strength

Active Publication Date: 2021-06-18
BEIJING CISRI GAONA TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The first purpose of the present invention is to provide a superalloy with low stacking fault energy, so as to solve the technical problem of contradiction between service performance and preparation process characteristics in the prior art

Method used

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  • High-temperature alloy with low stacking fault energy, structural part and application of high-temperature alloy
  • High-temperature alloy with low stacking fault energy, structural part and application of high-temperature alloy

Examples

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preparation example Construction

[0090] In a specific embodiment of the present invention, the preparation method of the forging comprises:

[0091] (a) distributing ingredients according to the low-stacking-fault-energy high-temperature alloy composition, and performing melting to obtain ingots;

[0092] (b) After homogenizing the ingot, forging and forming, and then performing heat treatment.

[0093] In a specific embodiment of the present invention, the conditions of the homogenization treatment include: heat preservation treatment at 1100-1150°C for 24-36 hours, and heat preservation treatment at 1170-1190°C for 36-48 hours.

[0094] In a specific embodiment of the present invention, the preparation method of the casting comprises:

[0095] According to the high-temperature alloy composition with low stacking fault energy, vacuum induction melting is carried out, heat treatment is carried out after casting, and castings are obtained.

[0096] In a specific embodiment of the present invention, the prepa...

Embodiment 1~7

[0104] Examples 1 to 7 respectively provide superalloys 1# to 7# and their preparation methods. The measured composition of superalloys is shown in Table 1. In addition, the alloy preparation methods of Comparative 1# to Comparative 3# are the same as those of Examples 1 to 7, except that the composition of the superalloy is different.

[0105] A method for preparing a superalloy, comprising the steps of:

[0106] (1) Weigh a certain amount of smelting raw materials that can obtain C, Co, Cr, W, Al, Ti, Nb, Ta, Mo, B, Zr, Fe, Mg and Ni elements according to the element ratio principle of superalloy, Including the base material and volatile elements, the base material is placed in the crucible of the vacuum induction furnace, and the volatile elements are placed in the feeder, and then vacuumed to start vacuum induction melting. When the vacuum degree is less than 3Pa, power on to heat up, and then refine for 40 minutes after full melting (gradually reduce the power) until the...

Embodiment 8

[0112]This embodiment provides a high-temperature alloy casting with low stacking fault energy, and its preparation method includes the following steps:

[0113] Referring to the element ratio principle of superalloy 1# in Example 1, the vacuum induction melting technology was used to cast according to a specific mold, followed by heat treatment to obtain a superalloy casting. The heat treatment conditions are: after 1100~1150°C for 2 hours, air cool to room temperature, then after 1050~1100°C for 2 hours, air cool to room temperature, then heat to 600~680°C for 20 hours, air cool, then heat to 750~800°C Cool to room temperature in air after 10 h.

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Abstract

The invention relates to the technical field of high-temperature alloys, in particular to a high-temperature alloy with low stacking fault energy, a structural part and application of the high-temperature alloy. The high-temperature alloy comprises, in percentage by mass, 0.01%-0.09% of C, 23.5%-27.5% of Co, 11%-15% of Cr, 0.1%-1.8% of W, 2.2%-2.6% of Al, 3.5%-5.5% of Ti, 0%-2% of Nb, 0%-2% of Ta, 2.1%-3.5% of Mo, 0.0001%-0.05% of B, 0.0001%-0.05% of Zr, 0%-2.5% of Fe, 0%-0.04% of Mg and the balance of Ni, wherein the sum of the mass fractions of Nb and Ta is greater than or equal to 0.8%. The high-temperature alloy has both service performance at 750 DEG C or above and good hot working characteristics, and can be applied to structural parts such as a turbine disc, a blade, a casing and a combustion chamber for long-time use.

Description

technical field [0001] The invention relates to the technical field of high-temperature alloys, in particular to a high-temperature alloy with low stacking fault energy, structural parts and applications thereof. Background technique [0002] The aero engine is the "heart" of the aircraft, known as the "crown jewel" of high-end manufacturing. High-temperature alloy materials are the cornerstone of aero-engines, and are also key materials in important weapons and equipment such as aerospace vehicles and naval gas turbines. In particular, general-purpose superalloys, due to their excellent service performance and good process applicability, can achieve "one material with multiple uses" and have outstanding cost performance. They are widely used in aviation, aerospace, ships and other fields. [0003] At this stage, the representative GH4169 alloy of general-purpose superalloy is the backbone superalloy material with the largest amount and widest application in various fields ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C19/05C22C30/00B33Y70/00B33Y80/00F01D5/02F01D5/28F01D25/00F01D25/24
CPCC22C19/056C22C30/00B33Y70/00B33Y80/00F01D5/02F01D5/28F01D25/005F01D25/24Y02P10/25
Inventor 毕中南于鸿垚杜金辉曲敬龙秦海龙甘斌
Owner BEIJING CISRI GAONA TECH
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