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Method for achieving forming of GH4738 nickel-base superalloy turbine discs

A technology of nickel-based high-temperature alloy and turbine disk, which is applied in the direction of engine components and mechanical equipment, can solve the problems of complex process and low efficiency, and achieve the effect of uniform grain size, stable operation and good grain structure

Inactive Publication Date: 2013-10-09
BC P INC CHINA NAT PETROLEUM CORP +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problems that the existing GH4738 nickel-based superalloy turbine disc preparation process is complicated, the efficiency is low, and it is difficult to obtain good quality, uniform grain size distribution, and no surface cracks.

Method used

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  • Method for achieving forming of GH4738 nickel-base superalloy turbine discs
  • Method for achieving forming of GH4738 nickel-base superalloy turbine discs
  • Method for achieving forming of GH4738 nickel-base superalloy turbine discs

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Embodiment 1

[0034] Embodiment 1: This embodiment proposes a method for realizing the forming of a GH4738 nickel-based superalloy turbine disk, and obtains better performance, which is characterized in that it specifically includes the following steps:

[0035] step 1:

[0036] 1) The regular Φ110mm×260mm cylindrical rod blank is hard-coated, the initial grain size is 150μm, and the actual composition of the selected GH4738 alloy is measured as C: 0.06; Al: 1.42; Ti: 3.15; Co: 13.5; Cr: 20.0; Mo: 4.1; Ni balance. a. First wrap the bar firmly with thermal insulation cotton; b. Then use a cut stainless steel plate (thickness 0.8mm) to hard wrap the outer side of the thermal insulation cotton, and weld the connection firmly.

[0037] 2) Heat the sheathed bar: a. Put the bar in the effective area of ​​the electric furnace, pad it with refractory bricks below, and control the heating temperature at 1080°C; b. Connect the external armored couple to the K type as required galvanic couple.

[0...

Embodiment 2

[0051] Embodiment 2: This embodiment proposes a method for realizing the forming of a GH4738 nickel-based superalloy turbine disk, and obtains better performance, which is characterized in that it specifically includes the following steps:

[0052] step 1:

[0053] 1) The regular Φ102mm×270mm cylindrical rod blank is hard-coated, the initial grain size is 160μm, and the actual composition of the selected GH4738 alloy is measured as C: 0.04; Al: 1.39; Ti: 3.05; Co: 13.3; Cr: 19.8; Mo: 4.05; Ni balance. a. First wrap the bar firmly with thermal insulation cotton; b. Then use a cut stainless steel plate (thickness 0.8mm) to hard wrap the outer side of the thermal insulation cotton, and weld the connection firmly.

[0054] 2) Heat the sheathed bar: a. Put the bar in the effective area of ​​the electric furnace, pad it with refractory bricks below, and control the heating temperature at 1060°C; b. Connect the external armored couple to the K type as required galvanic couple.

[...

Embodiment 3

[0063] This embodiment proposes a method to realize the forming of GH4738 nickel-based superalloy turbine disc, and obtains better performance. The difference between the forming process and Example 1 lies in step (2): the cake base obtained in step 1 is subjected to the following die forging process Control: a. Firstly, hard wrap the biscuit as shown in 1); b. Put the wrapped biscuit in the effective area of ​​the electric furnace, pad it with refractory bricks below, and control the heating temperature at 1080°C ; c. Connect the external armored couple as required, K-type galvanic couple; d. After adjusting the preheated mold on the press, use water lubricant to lubricate the mold cavity to ensure that the temperature is above 350 ° C; e. After the forging billet reaches the set temperature completely, the cake is quickly transferred to the mold of the press after being released from the furnace, and the cake is placed in the middle of the mold, and the transfer time is contr...

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Abstract

The invention discloses a method for achieving forming of GH4738 nickel-base superalloy turbine discs, and relates to a method for preparing the GH4738 nickel-base superalloy turbine discs. The method aims at solving the problems that an existing technology for preparing the GH4738 nickel-base superalloy turbine discs is complex and low in efficiency, and cannot achieve the purposes that the turbine discs are good in quality, even in grain distribution and free of surface crack. The method for achieving forming of the GH4738 nickel-base superalloy turbine discs comprises the following steps: adopting a compound insulation method with a sheath and insulation cotton, carrying out double-firing-number heating, upsetting and die forging, and carrying out solidifying solution and double aging processing at the subsolid solution temperature. By means of the method, the GH4738 nickel-base superalloy turbine discs with different diameter dimensions and disc thicknesses can be prepared. The method can be applied to preparation of nickel-base superalloy turbine discs in the field of petrochemical engineering and aerospace, and preparation of other disc forge pieces used under the high temperature condition.

Description

[0001] technical field [0002] The invention relates to the field of turbine disc forming of nickel-based deformed superalloy, which is used for long-term use at around 720°C, and requires high temperature strength, long-lasting creep, fatigue and crack growth rate under severe stress conditions. A method for forming a nickel-based superalloy turbine disk. Background technique [0003] In the field of petrochemical industry, the flue gas turbine developed by using the thermal energy of refinery tail gas to generate electricity is a product with great market prospects at home and abroad, which has created huge benefits for the development of the national economy; at the same time, aerospace engines urgently need turbines that can withstand high temperatures and high strength. Disk parts, whether it is a key turbine disk part used in a flue gas turbine or an aerospace engine, the important material for manufacturing the high-temperature hot end part is mainly GH4738 nickel-ba...

Claims

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Application Information

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IPC IPC(8): B21K3/00
Inventor 姚志浩董建新张麦仓
Owner BC P INC CHINA NAT PETROLEUM CORP
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