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Forging method of GH4169 series high temperature alloy turbine disc for aero-engine

A GH4169, aero-engine technology, applied in the field of thermal processing of nickel-based high-temperature alloy discs, can solve the problems of large cross-sectional drop, large performance difference, and difficulty in ensuring the uniformity of the structure of the wheel hub and rim, and achieve uniform and fine structure, room temperature mechanics Excellent performance and high temperature mechanical properties

Active Publication Date: 2019-04-16
SHAANXI HONGYUAN AVIATION FORGING
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] Due to the long-term working conditions of high temperature and high pressure, the turbine disk parts of aero-engines have very harsh working conditions and have very strict requirements on the structure and performance of the parts, but their structure is very simple. The turbine disk body includes two parts: the hub and the rim. Through holes, the axial dimension of the hub is 1.5 to 3 times that of the rim, and the cross-sectional drop is large. Using conventional forging methods, it is difficult to ensure the uniformity of the structure of the hub and the rim, and the performance difference is large, which is difficult to meet the requirements of the parts.

Method used

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  • Forging method of GH4169 series high temperature alloy turbine disc for aero-engine
  • Forging method of GH4169 series high temperature alloy turbine disc for aero-engine

Examples

Experimental program
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Embodiment 1

[0018] Such as figure 1 As shown, the forging of a low-pressure turbine disc of an engine is made of GH4169G, the weight of the forging is 160kg, the outline size of the forging is φ547×137mm, and the GH4169G alloy bar of φ250×420mm is selected.

[0019] First, heat the above-mentioned GH4169G alloy bar to 850°C for 250 minutes, then raise the temperature to 995°C and hold for 200 minutes, then take it out of the furnace, upsetting the height to 200mm, and then radially stretch it to 205×490; The height is upsetting to 360mm, and then drawn and rolled to φ250×420mm; the hammer anvil is preheated to 250°C during the forging process, and the forging equipment is a 2500T fast forging machine.

[0020] Heat the above billet to 850°C for 250min, then heat it up to 1000°C for 200min, take it out of the furnace, heat it for 30min, and carry out pre-forging. The pre-forging mold is preheated to 300°C, and the forging speed is 5mm / s. Grinding after forming.

[0021] Such as figure ...

Embodiment 2

[0024] The present invention will be further described in detail below through specific examples.

[0025] The low-pressure turbine disk forging of an engine is made of GH4169 material, the feeding weight is 320kg, the forging outline size is φ635×157mm, and the GH4169 alloy bar of φ300×550mm is selected.

[0026] First, heat the above-mentioned GH4169 alloy bar to 850°C for 300 minutes, then raise the temperature to 1000°C and hold it for 240 minutes, then take it out of the furnace, upsetting the height to 280mm, and then radially stretch it to 240×670; The height is upsetting to 500mm, and then the length is drawn and rounded to φ300×550mm; the hammer and anvil is preheated to 250°C during the forging process, and the forging equipment is a 2500T fast forging machine.

[0027] Heat the above billet to 850°C for 300min, then raise the temperature to 990°C for 240min, take it out of the furnace, heat it for 50min, and carry out pre-forging. The pre-forging mold is preheated t...

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Abstract

The inventionrelates a forging method of a GH4169 series high temperature alloy turbine disc for an aero-engine. The forging method is characterized by comprising the steps that 1, die steel is adopted for producing two sets of dies, one set of the two sets of dies is a finishing forging die, and the other set of the two sets of dies is a pre-forging die; 2, blank making and one-time forging are carried out, a GH4169 series high temperature alloy bar material is selected, a bar material with the required length is cut off, the bar material is heated to 980 DEG C-1010 DEG C and heated through,discharging is carried out to complete40%-70% of upsetting and deformation, drawing out in the four-direction radial direction is carried out, and finally the length-width ratio of the blank materialis largerthan 2; 3, blank making and second-time forging are carried out, the blank material is heated to 980 DEG C-1010 DEG C and heated through, discharging is carried out to complete 20%-30% upsetting and deformation, drawing out and rolling are carried out to the bar material size in the step 2, and air cooling is carried out to the room temperature;4, pre-forging is carried out, the blank material is heated to 990 DEG C-1010 DEG C, discharging is carried out after through heating, and soft package sheathing is carried out; and 5, finish forging is carried out, after pre-forged blank material is subjected to hard package sheathing, heating is carried out to 990 DEG C-1020 DEG C, thepre-forged blank material is placed in the finishing forging die after through heating, final forging andforming are carried out, and the forging rate is 5mm / s-10mm / s.

Description

technical field [0001] The invention relates to the technical field of thermal processing of nickel-based superalloy discs. Background technique [0002] Due to the long-term working conditions of high temperature and high pressure, the turbine disk parts of aero-engines have very harsh working conditions and have very strict requirements on the structure and performance of the parts, but their structure is very simple. The turbine disk body includes two parts: the hub and the rim. Through holes, the axial dimension of the hub is 1.5 to 3 times that of the rim, and the cross-sectional drop is large. Using conventional forging methods, it is difficult to ensure the uniformity of the structure of the hub and the rim, and the performance difference is large, which is difficult to meet the requirements of the parts. Contents of the invention [0003] The technical problem to be solved by the invention is to provide a nickel-base superalloy turbine disc forging with uniform str...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21K1/32
CPCB21K1/32
Inventor 唐军操贻高张帅王彦伟刘东何森虎
Owner SHAANXI HONGYUAN AVIATION FORGING