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Precision forging method of GH4720Li high-temperature alloy blade and blade forge piece thereof

A superalloy and precision forging technology is applied in the processing field of superalloy blades, which can solve the problems of high difficulty of blades and narrow hot working window of hard-to-deform superalloys, achieve small machining removal, solve the problem of insufficient use temperature and high utilization rate. high effect

Active Publication Date: 2022-07-19
CENT IRON & STEEL RES INST +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the narrow thermal processing window of difficult-to-deform superalloys, it is more difficult to prepare blades by precision forging
[0004] At present, there is no report on the production of high-temperature alloy compressor blades that are difficult to deform by using precision forging technology. Therefore, it is more necessary to study the preparation process of GH4720Li alloy blades to ensure the quality of engine blade products and provide higher pass rate, better performance and lower cost. Lower hard-to-deform superalloy blades

Method used

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  • Precision forging method of GH4720Li high-temperature alloy blade and blade forge piece thereof
  • Precision forging method of GH4720Li high-temperature alloy blade and blade forge piece thereof
  • Precision forging method of GH4720Li high-temperature alloy blade and blade forge piece thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0128] The 100 times grain photo of the blade body position of the GH4720Li superalloy blade forging obtained in Example 1 is as follows figure 1 shown, the high magnification photo of the tenon position is shown in figure 2 shown. like figure 1 shown, the grain size is 12.5; as figure 2 As shown, the grain size is 11 grades. As shown in the figure, the grain size distribution of the blade forging in Example 1 is uniform, and there are no obvious coarse grains, bands and defects.

Embodiment 2

[0129] The 100 times grain photo of the blade body position of the GH4720Li superalloy blade forging obtained in Example 2 is as follows image 3 shown, the high magnification photo of the tenon position is shown in Figure 4 shown. like image 3 shown, the grain size is 11; as Figure 4 As shown, the grain size is 11 grades. As shown in the figure, the grain size distribution of the blade forging in Example 2 is uniform, and there are no obvious coarse grains, bands and defects.

Embodiment 3

[0130] The 100 times grain photo of the blade body position of the GH4720Li superalloy blade forging obtained in Example 3 is as follows Figure 5 shown, the high magnification photo of the tenon position is shown in Image 6 shown. like Figure 5 shown, the grain size is 12.5, as Figure 4 As shown, the grain size is 12 grades. As shown in the figure, the grain size distribution of the blade forging in Example 3 is uniform, and there are no obvious coarse grains, bands and defects.

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Abstract

The invention relates to a precision forging method for a GH4720Li high-temperature alloy blade and a blade forge piece obtained through the precision forging method. The precision forging method comprises the steps that a GH4720Li alloy bar material section is pretreated, and a preformed blank is obtained; the method comprises the steps that the prefabricated blank is subjected to precision forging treatment, the precision forging treatment comprises one-heating-number extrusion, one-heating-number head upsetting, one-heating-number pre-forging and one-heating-number finish forging, the extrusion treatment comprises the steps that the prefabricated blank is subjected to heating treatment, then the prefabricated blank is transferred into a mold to be subjected to extrusion forging, and the transferring and extrusion forging processes are completed within 8 seconds. The mechanical property of the blade forge piece obtained through the precision forging method is more suitable for being used under the condition of 700-750 DEG C, and the problem that the use temperature of an engine blade is insufficient at the present stage is solved.

Description

technical field [0001] The invention relates to the processing of superalloy blades, in particular to a precision forging method for GH4720Li superalloy blades and blade forgings obtained therefrom. Background technique [0002] With the development of aero-engines, the service temperature of the final stage rotor blades of the high-pressure compressor of the new engine has reached more than 700 ℃, which is close to the service limit of nickel-based superalloys. In order to meet the high performance, high stability and reliability of the engine, the performance of the GH4169 alloy that can be used stably below 650 °C can no longer meet the service requirements. Therefore, the use of new alloys such as GH4720Li alloy as the blade material used above 700 ℃ has become a new choice. The long-term service temperature of GH4720Li alloy can reach 700℃-750℃. It has high high temperature strength, good fatigue and creep properties, and excellent corrosion resistance and oxidation re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21J5/00B21J1/00B21J1/06B21K3/04
CPCB21J5/002B21J1/00B21J1/06B21K3/04
Inventor 曲敬龙杜金辉史玉亭张国栋陈佳语谷雨安腾孟令胜唐超邓群
Owner CENT IRON & STEEL RES INST
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