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Integral die forging method for large gh4169 turbine shaft

A GH4169, integral mold technology, applied in the direction of mechanical equipment, engine components, etc., can solve the problems of large-scale GH4169 turbine shaft forgings such as uniformity, overall stability and poor dimensional accuracy, and achieve reduced material consumption, high uniformity, Regular and beautiful appearance

Active Publication Date: 2018-11-16
SHAANXI HONGYUAN AVIATION FORGING
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The technical problem to be solved by the present invention is: in order to solve the problem of poor structure uniformity, integrity, stability and dimensional accuracy of the large GH4169 turbine shaft forging

Method used

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  • Integral die forging method for large gh4169 turbine shaft
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  • Integral die forging method for large gh4169 turbine shaft

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Embodiment Construction

[0024] Select the production and development of a certain type of aircraft turbine shaft forging below, and describe the process steps of the present invention in detail.

[0025] A method for integral die forging of a large GH4169 turbine shaft is provided, comprising the following steps:

[0026] Step 1. Heating the alloy bar at a heating temperature of 1000°C to 1010°C. After heating, upsetting one end of the bar through a tire mold to form a flange to obtain an upsetting bar. The deformation of the upsetting is more than 30%;

[0027] Step 2. Heat the upsetting bar to 1000℃~1010℃, and lengthen the unupset part of the bar into a rod. After the elongation, the cross section of the rod is flat and square; after that, forge the flange, and forge the flange The cross-section of the blank is oblate, and the blank is obtained, and the deformation of the blank relative to the upsetting bar is more than 20%;

[0028] Step 3: Carry out mechanical processing on the blank to ensure t...

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Abstract

The invention relates to an integral die forging method for a large-scale GH4169 alloy turbine shaft (the length of the shaft is 1520 mm). In general, two forging methods are adopted for large-scale shaft type forge pieces, and include the axial drawing-out free forging method and the comprehensive forging method combining rod portion local free drawing-out with flange local (forming) die forging. A shaft forging piece manufactured through the axial drawing-out free forging method is generally characterized by being uneven in deformation, large, poor in coaxiality and cylindricity, serious in warping, and low in production efficiency; compared with the shaft forging piece manufactured through the axial drawing-out free forging method, a shaft forging piece manufactured through the comprehensive forging method combining rod portion local free drawing-out with flange local (forming) die forging has similar characteristics, flange part forming is slightly superior, however, a transitional structure is inevitably generated in partial forging, and thus the whole performance of a forging piece of the turbine shaft is greatly lowered. According to the integral die forging method for the large-scale GH4169 turbine shaft, the technology thinking of partial crude manufacturing and whole die forging forming is adopted, the structure homogeneity, integrality and product stability of the shaft forging piece of the GH4169 alloy turbine shaft can be effectively improved, and production efficiency is greatly improved.

Description

Technical field: [0001] The invention belongs to the technical field of thermal processing of superalloys, and relates to an integral die forging method of a large GH4169 turbine shaft. Background technique: [0002] The GH4169 alloy is a nickel-based superalloy that is precipitated and strengthened by body-centered square γ" and face-centered cubic γ' phases. It has good comprehensive properties in the temperature range of -253 to 700 ° C, and its yield strength below 650 ° C ranks among the highest deformation temperatures. The first alloy, and has good fatigue resistance, radiation resistance, oxidation resistance, corrosion resistance, as well as good processing performance, welding performance and long-term structural stability, and can manufacture various parts with complex shapes. The structure of the alloy has great influence on The thermal processing process is particularly sensitive. By mastering the phase precipitation and dissolution laws in the alloy and the rel...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B21K1/06
CPCB21K1/06
Inventor 王国强薛强甄小辉秦卫东何森虎
Owner SHAANXI HONGYUAN AVIATION FORGING
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