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A Method for Improving Microstructure and High Temperature Smooth Fatigue Properties of gh4698 Disc Forging

A technology for forgings and alloy discs, which is applied in the field of thermal processing of high-temperature alloys, can solve problems such as coarse grains, unstable high-temperature smooth fatigue performance, poor structure uniformity of GH4698 disc forgings, etc., and achieve the effect of solving uneven and uniform structures

Active Publication Date: 2018-10-12
SHAANXI HONGYUAN AVIATION FORGING
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The technical problem to be solved by the present invention is: in order to solve the problems of poor microstructure uniformity, coarse crystal grains and unstable high-temperature smooth fatigue performance of GH4698 disc forgings

Method used

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Embodiment Construction

[0018] Select the production and development of a turbine disk forging of a certain type of aircraft below, and describe the process steps of the present invention in detail.

[0019] A forging method for a GH4698 alloy disc forging is provided, comprising the following steps:

[0020] Step 1. Heat the bar to 800°C with a thermal insulation coefficient of 0.8mm / min, then raise the temperature to 990-1000°C with a thermal insulation coefficient of 0.8mm / min at a heating rate of 50-70°C / min, then raise the temperature to 1100-1120°C, and the thermal insulation coefficient is 0.8mm / min; then, the heated bar is covered with aluminum silicate thermal insulation cotton, and kept at 1100-1120°C for 30 minutes;

[0021] Step 2. Perform multi-fire upsetting on the sheathed bar to obtain a blank, ensuring that the deformation per fire is 25% to 35%. Step 3. Perform multi-fire die forging on the blank to obtain a forging and air-cool it. Guarantee that the amount of deformation per fire...

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Abstract

The invention relates to a method for improving the structure and high-temperature smooth fatigue performance of a GH4698 disk forge piece. Under normal conditions, production of the GH4698 disk forge piece needs the multiple procedures of upsetting cake blank making, die forging, secondary solid solution treatment and aging heat treatment, wherein the blank making and die forging procedures further comprise forging heating and deformation procedures. Formulation of all heating procedures shall follow the structure change characteristics of GH4698 materials during heating, and the internal relation between nominal deformation and real deformation of all areas shall also be fully understood during formulation of all deformation procedures. The method is started with setting of GH4698 heating parameters, deformation step distribution and other aspects emphatically, the structure of the GH4698 disk forge piece can be effectively refined and homogenized, and finally the high-temperature smooth fatigue performance of the GH4698 disk forge piece is improved.

Description

Technical field: [0001] The invention belongs to the technical field of thermal processing of high-temperature alloys, and relates to a method for improving the microstructure and high-temperature smooth fatigue performance of a GH4698 disc forging. Background technique: [0002] GH4698 is a nickel-based superalloy strengthened by aluminum, titanium, molybdenum, niobium and other elements. It is developed on the basis of GH4033 alloy by supplementary alloying. It has high durability and good comprehensive performance in the range of 500-800 °C. . The alloy is widely used in the manufacture of important load-bearing parts such as turbine disks, compressor disks, deflectors, and load-bearing rings of aero-engines. The working temperature can reach 750~800℃. [0003] The formulation of all heating procedures of GH4698 products for aero-engines should follow the structure change characteristics of GH4698 materials during heating; at the same time, the formulation of all deform...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C22F1/10
CPCC22F1/10
Inventor 王国强秦卫东甄小辉何森虎
Owner SHAANXI HONGYUAN AVIATION FORGING