Hot working process of GH4738 nickel-based superalloy

Abstract

The invention discloses a hot working process of a GH4738 nickel-based superalloy. The process comprises the following steps that A, the GH4738 nickel-based superalloy is taken as a raw material, and is smelted by adopting a vacuum induction melting (VIM) process and a vacuum consumable remelting (VAR) process in sequence to obtain a vacuum consumable ingot; B, the vacuum consumable ingot is subjected to homogenization treatment and cogging forging treatment, and a GH4738 alloy bar blank is obtained; C, the GH4738 alloy bar blank is put into a gas furnace to be heated along with the furnace, flat anvil upsetting is conducted through a forging hammer after heat preservation, and a GH4738 alloy disc forge piece is obtained; and D, the GH4738 alloy disc forge piece is sequentially subjected to solution treatment, stabilizing treatment and secondary aging treatment, and the GH4738 nickel-based high-temperature alloy uniform in grain size and excellent in high-temperature erosion performance is obtained. According to the hot working process, the phenomena of mixed crystals, coarse crystals and the like in a GH4738 high-temperature alloy deformation structure can be avoided, the overall hardness and high-temperature erosion performance of a final forge piece are improved, and meanwhile the yield of the forge piece is increased.

Description

technical field [0001] The invention relates to the technical field of thermal processing of nickel-based alloys. Specifically, it is a hot working process of GH4738 nickel-based superalloy. Background technique [0002] Turbine disk is an important part of gas turbine and aero-engine, and its performance directly affects the product quality of gas turbine and aero-engine. Previously, the material of the turbine disk was GH4169 from research and development to production, but it was found that the alloy was deformed during high-temperature service and could not be used normally. It cannot be used normally at temperatures exceeding 650°C. In such a situation, researchers have conducted research on alloys such as GH4864 and GH4738. As early as 1952, Special Metal successfully developed a high-temperature alloy with γ′ phase precipitation hardening as the hardening method by vacuum smelting method, and made turbine disks below 800 °C in the 1960s and used them on Boeing 727 ...

AI Technical Summary

Problems solved by technology

[0003] For this reason, the technical problem to be solved by the present invention is to provide a thermal processing process of GH4738 nickel-based superalloy, to solve the phenomenon of mixed crystals and coarse grains easily appearing in the deformed structure of current GH4738 nickel-based superalloy and the deformation process. cracking and other problems; to make the GH4738 nickel-based superalloy have the characteristics of low corrosion and wear rate and high hardness, improve the overall hardness and high-temperature erosion performance of the final alloy disc forging, and also improve the yield of the forging to meet the service life of the turbine disc required

Images