Forging method of GH4586 high-temperature alloy

A technology of GH4586 and superalloy, applied in the field of blade forging, can solve the problems of sensitive deformation process parameters, large deformation resistance, narrow deformation temperature range, etc., and achieve the effect of ensuring dimensional consistency

Active Publication Date: 2019-11-12
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] GH4586 has high degree of alloying, high deformation resistance, and narrow deformation temperature range, so it is very difficult to form by thermal processing
In particular, the microstructure

Method used

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  • Forging method of GH4586 high-temperature alloy
  • Forging method of GH4586 high-temperature alloy
  • Forging method of GH4586 high-temperature alloy

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0043] Step 1: Surface treatment is carried out on the original bar of the superalloy, and a high-temperature-resistant glass coating is applied; the thickness of the high-temperature-resistant glass coating is 0.06 mm; the diameter of the original bar is 60 mm.

[0044] Step 2, final forging

[0045] Heat the original high-temperature alloy bar to 1135°C in an electric furnace for 54 minutes; while heating the original high-temperature alloy bar, preheat the mold base and the mold to 200°C, after the mold is heated, before the bar is placed inside the mold , spray graphite lubricant on the inner surface of the mold for lubrication, and then put the bar into the mold; then use the final forging die to forge on the electric screw press to obtain the final forging; in this embodiment, from the high temperature original bar to The deformation of the final forging is 50%.

[0046] Step 3, solution heat treatment, heating the final forging to 1070°C, keeping it warm for 4h+15min, ...

Embodiment 2

[0052] Step 1, surface-treating the original bar of the superalloy, and coating it with a high-temperature-resistant glass coating; the thickness of the high-temperature-resistant glass coating is 0.06mm; the diameter of the original bar is 50mm;

[0053] Step 2, final forging

[0054] Heat the original high-temperature alloy bar to 1120°C in an electric furnace for 40 minutes; while heating the original high-temperature alloy bar, preheat the mold base and mold to 195°C, after the mold is heated, put the bar into the mold , spray graphite lubricant on the inner surface of the mold for lubrication, and then put the bar into the mold; then use the final forging die to forge on the electric screw press to obtain the final forging; in this embodiment, from the high temperature original bar to The deformation of the final forging is 35%.

[0055] Step 3, solution heat treatment, heating the final forging to 1060°C, keeping it warm for 4h+30min, and then oil cooling to room temper...

Embodiment 3

[0058] Step 1. Surface treatment is carried out on the original bar of the superalloy, and a high-temperature-resistant glass coating is applied; the thickness of the high-temperature-resistant glass coating is 0.05 mm; the diameter of the original bar is 70 mm.

[0059] Step 2, final forging

[0060] Heat the original high-temperature alloy bar to 1090°C in an electric furnace for 70 minutes; while heating the original high-temperature alloy bar, preheat the mold base and the mold to 205°C, after the mold is heated, before the bar is put into the mold , spray graphite lubricant on the inner surface of the mold for lubrication, and then put the bar into the mold; then use the final forging die to forge on the electric screw press to obtain the final forging; in this embodiment, from the high temperature original bar to The deformation of the final forging is 40%.

[0061] Step 3, solution heat treatment, heating the final forging to 1075°C, keeping it warm for 4h+45min, and t...

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Abstract

The invention discloses a forging method of a GH4586 high-temperature alloy. For a GH4586 high-temperature alloy forge piece, the surface of the forge piece is firstly coated with a high temperature resisting glass coating, and the surface of the forge piece is prevented from being oxidized or cracking in the forging process; in the forging process, an electric spiral press machine is adopted forforging for the first time, the blow energy and deformation of the forge piece can be precisely controlled, the forge piece achieves precise deformation, size consistency is high, meanwhile, a more uniform structure is obtained, and then good mechanical performance is obtained; and the spiral press machine is more stable than a forging hammer, the blow energy can be strictly controlled, forge piece flow lines can be uniformly distributed along the appearance, and the mechanical performance is greatly improved. In the forging method, an electric furnace is adopted for heating both during advanced heating and subsequent heat treatment of the forge piece, and the heating temperature can be precisely controlled within the range of +/-10 DEG C.

Description

【Technical field】 [0001] The invention belongs to the field of blade forging, and in particular relates to a GH4586 superalloy forging method. 【Background technique】 [0002] With the continuous advancement of aero-engine technology, aero-engine blades, as one of the key parts of the engine, have continuously improved material performance requirements. [0003] GH4586 alloy is a typical hard-to-deform nickel-based superalloy. The alloy exhibits excellent mechanical and physical properties below 650 °C, which meets the comprehensive performance requirements of aero-engine blades, and has been used to manufacture various types of high-temperature rotating parts of rocket engines. [0004] GH4586 has high degree of alloying, high deformation resistance, and narrow deformation temperature range, so it is very difficult to form by thermal processing. In particular, the microstructure of forgings is sensitive to deformation process parameters, and abnormal structures caused by i...

Claims

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Application Information

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IPC IPC(8): B21K3/04B21J3/00B21J1/06
CPCB21J1/06B21J3/00B21K3/04
Inventor 王鹏王周涛张卓荦蒋彦骏李娜陈康康马军刘宁
Owner AECC AVIATION POWER CO LTD
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