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Deformed superalloy and method for its preparation, hot end rotating part of engine and engine

A technology for deforming superalloys and rotating parts, which is applied in the direction of engine components, machines/engines, mechanical equipment, etc. It can solve problems such as unsatisfactory performance and high cost of alloys, and achieve good uniformity and high ultrasonic detectability.

Active Publication Date: 2021-03-23
BEIJING CISRI GAONA TECH +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, on the one hand, the current alloy cannot meet the performance requirements above 800 °C, and at the same time, the powder metallurgy process makes the obtained alloy have a higher cost

Method used

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  • Deformed superalloy and method for its preparation, hot end rotating part of engine and engine
  • Deformed superalloy and method for its preparation, hot end rotating part of engine and engine
  • Deformed superalloy and method for its preparation, hot end rotating part of engine and engine

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preparation example Construction

[0057] In another aspect of the present invention, the present invention provides a method for preparing the aforementioned deformed superalloy, comprising the following steps, for details, refer to figure 1 :

[0058] Carrying out vacuum induction smelting, electroslag remelting continuous directional solidification smelting, blank opening, forging, die forging forming and heat treatment on the mixture of each component in sequence to obtain the deformed superalloy;

[0059] Wherein, the heat treatment includes solution heat treatment and aging heat treatment, the temperature of the solution heat treatment is 1100-1180°C (such as 1100°C, 1120°C, 1140°C, 1160°C or 1180°C, etc.), the aging heat treatment The temperature is 760-815°C (for example, it can be 760°C, 780°C, 800°C or 815°C, etc.).

[0060] The above-mentioned preparation method is simple, convenient, and easy to implement. There is no harmful phase precipitation in the preparation process to obtain an ideal microst...

Embodiment 1

[0080] The deformed superalloy includes components with the following mass fractions: Co 20.4%; Cr 13.1%; Mo 4.1%; W 2.2%; Al 3.3%; Ti 3.75%; Nb 1.0%; Ta 2.45%; 0.018%; C 0.020%; Zr 0.050%; Hf 0.001%; ​​Y 0; Fe 0.1%;

[0081] The preparation method of deformed superalloy is as follows:

[0082] 1) Raw materials are prepared according to the proportion of each component, and the master alloy electrode rod is smelted in a vacuum induction furnace;

[0083] 2) Electrode rods are head-cut, tail-removed, and polished, followed by electroslag remelting and continuous directional solidification to prepare directional solidified ingots with a diameter of 260mm, and there are no equiaxed grains in the core of the ingot's macroscopic longitudinal low-magnification structure;

[0084] 3) The directionally solidified ingot is subjected to high-temperature homogenization heat treatment, and the homogenization maximum temperature is 1195°C, and it is kept for 12 hours;

[0085] 4) The ingot...

Embodiment 2

[0090] The composition of the deformed superalloy is the same as in Example 1, except that the total content of Ti and Al is 6.5%, and the mass ratio of Ti and Al is 1.

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Abstract

The invention provides a deformed high-temperature alloy, a preparation method of the deformed high-temperature alloy, an engine hot end rotating part and an engine, and relates to the field of nickel-based high-temperature alloy. The deformed high-temperature alloy is prepared from the following components in percentage by mass: 19.0%-22.0% of Co, 10%-16% of Cr, 3.0%-5.0% of Mo, 1.5%-3.5% of W, 2.4%-3.8% of Al, 3.0%-4.5% of Ti, 0.5%-1.5% of Nb, 1.0%-3.0% of Ta, 0.010%-0.040% of B, 0.005%-0.060% of C, 0.030%-0.060% of Zr, 0.0%-0.6% of V, 0.0%-0.3% of Hf, 0.0%-0.01% of Y, 0.0%-1.5% of Fe, 0%-0.5% of inevitable impurities and the balance of Ni. The total mass fraction of Al, Ti, Nb, Ta and V is 9.5%-12.5%. The deformed high-temperature alloy can meet the requirements of high performance, high homogeneity, and low cost for domestic aviation and aerospace equipment, especially hot-end rotating parts such as engine turbine disks.

Description

technical field [0001] The invention relates to the technical field of nickel-based superalloys, in particular to a deformed superalloy and a preparation method thereof, a hot end rotating part of an engine and an engine. Background technique [0002] With the improvement of the thermal efficiency of advanced aero-engines and the strict requirements of fuel economy and low pollutant emissions, the temperature bearing capacity of nickel-based superalloy materials for turbine disks is also increasing, such as the first generation of nickel-based turbine disk alloy bearings The temperature capacity reaches 680-700°C for a short time, and the representative alloys include Rene95, FGH95, GH4169 and other alloys; the temperature capacity of the second-generation nickel-based turbine disc alloy reaches 730-750°C for a short time, and the representative alloys include Rene88DT, Udimet720Li, Rene65, Alloys such as FGH96; the short-term service temperature of the third-generation turb...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C22C19/05C22C1/02C22F1/10F01D5/02
CPCC22C1/023C22C19/056C22F1/002C22F1/10F01D5/02
Inventor 李福林钟世林谭海兵付锐何爱杰马川田伟钟燕孟令超曲敬龙贾建杜金辉冯滌
Owner BEIJING CISRI GAONA TECH
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