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Nickle-cobalt based high temperature alloy turbine disk and preparation method thereof

A superalloy, turbine disk technology, applied in mechanical equipment, engine components, machines/engines, etc., can solve the problems of fatigue cracks, creep failure, and short service life of turbine disks, and achieve long service life and creep resistance. The effect of synergistically improving and reducing cutting difficulty

Active Publication Date: 2020-08-18
INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the inventors of the present invention have found that the turbine discs processed by the above-mentioned surface treatment technology tend to form fatigue cracks or creep failures during service, and the service life is relatively short.

Method used

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  • Nickle-cobalt based high temperature alloy turbine disk and preparation method thereof
  • Nickle-cobalt based high temperature alloy turbine disk and preparation method thereof
  • Nickle-cobalt based high temperature alloy turbine disk and preparation method thereof

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preparation example Construction

[0060] In one aspect, the present invention provides a method for preparing a nickel-cobalt-based superalloy turbine disk, which specifically includes the following steps:

[0061] Solution treatment: The hot die forged turbine disc blank is solution treated at a temperature of 0.75-0.95Tm (Tm is the melting point temperature of the nickel-cobalt-based superalloy) for 2-10h, and then the oil is cooled to room temperature (here, hot The turbine disk blank formed by die forging can also be replaced by the turbine disk blank formed by isothermal forging).

[0062] Cutting and rough machining treatment: the solid solution treated turbine disc blank is subjected to rough cutting, and the target size of the rough machining is 4-10mm more than the final size of the turbine disc. According to the outline drawing of the turbine disk, the position of the center hole of the turbine disk needs to be aligned, and the rough cutting of the surface of the turbine disk blank after solid soluti...

Embodiment 1

[0081] Embodiment 1 prepares a kind of nickel-cobalt-based superalloy turbine disc, and the specific steps are as follows:

[0082] Preparation of hot forged turbine disk billet: vacuum induction melting, electroslag remelting and vacuum induction consumable melting are carried out on the raw materials (see the above alloy composition for the ratio of raw materials) to obtain triple smelting ingots. After cutting the head and tail of the ingot and grinding the surface, first homogenize it at a temperature of 1120°C for 16 hours, and then homogenize it at a temperature of 1210°C for 8 hours. The ingot after the homogenization treatment is soft-coated, and the billet forging is carried out by using a fast forging machine (wherein, the initial forging temperature is 1140° C., and the final forging temperature is higher than 850° C.) to obtain a dual-phase fine-grained rod with uniform structure. The sawing machine is used for blanking, and the forging equipment is further used to...

Embodiment 2

[0090] Embodiment 2 prepares a kind of nickel-cobalt-based superalloy turbine disc, and the specific steps are as follows:

[0091] Preparation of hot forged turbine disk billet: vacuum induction melting, electroslag remelting and vacuum induction consumable melting are carried out on the raw materials (see the above alloy composition for the ratio of raw materials) to obtain triple smelting ingots. After cutting the head and tail of the ingot and grinding the surface, first homogenize it at a temperature of 1120°C for 16 hours, and then homogenize it at a temperature of 1210°C for 8 hours. The ingot after the homogenization treatment is soft-coated, and the billet forging is carried out by using a fast forging machine (wherein, the initial forging temperature is 1140° C., and the final forging temperature is higher than 850° C.) to obtain a dual-phase fine-grained rod with uniform structure. The sawing machine is used for blanking, and the forging equipment is further used to...

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Abstract

The invention discloses a nickle-cobalt based high temperature alloy turbine disk and a preparation method thereof. According to the technical scheme, the surface layer of the nickle-cobalt based hightemperature alloy turbine disk is provided with microtwinning and is in the compressive stress state. The preparation method comprises carrying out surface treatment on a forged formed turbine disk billet to obtain the nickle-cobalt based high temperature alloy turbine disk; and surface treatment comprises the following steps: sequentially carrying out solution treatment, cutting rough machining,aging treatment, thermal shot blasting treatment and thermal mechanical surface treatment on the forged formed turbine disk billet to obtain the nickle-cobalt based high temperature alloy turbine disk. According to the invention, microtwinning is mainly introduced to the surface layer of the turbine disk to enhance the creep and fatigue resistance performance of the surface layer of the turbine disk to prolong the service life of the turbine disk.

Description

technical field [0001] The invention relates to the technical field of a turbine disk, in particular to a nickel-cobalt-based superalloy turbine disk and a preparation method thereof. Background technique [0002] The turbine disk is an important hot-end part of a modern aero-engine, its main function is to fix the turbine blades and transmit power; the turbine disk works under the extreme environment of complex temperature load, centrifugal load and aerodynamic load. With the gradual development of aero-engines in the direction of high performance, high reliability, long life, and large-scale, the temperature-bearing capacity and mechanical performance requirements for key components such as aero turbine disks are also increasing, and the turbine disks often suffer from increased internal stress. Large, the surface quality is unqualified, and it will fail due to cracking or excessive deformation under repeated loads. [0003] In order to meet the development needs of advan...

Claims

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Application Information

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IPC IPC(8): C22C19/05C22C30/00C22F1/10F01D5/02B23P15/14
CPCB23P15/14C22C19/055C22C19/056C22C30/00C22F1/10F01D5/02
Inventor 张瑞崔传勇周亦胄孙晓峰
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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