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Titanium alloy smithing technological parameter testing method

A test method and technology of process parameters, applied in the field of metal material science, can solve the problems of few places to cut mechanical performance samples, complex forging shapes, and inability to quantitatively study deformation, etc.

Active Publication Date: 2008-10-29
BEIJING AVIATION MATERIAL INST NO 1 GRP CORP CHINA AVIATION IND +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The test results obtained by this method can represent the real performance level of the alloy under different forging processes, but there are also shortcomings, mainly including: (a) It is impossible to quantitatively study the influence of deformation on the mechanical properties of forgings, because most of the forgings on the aircraft are In the form of high-reinforced thin-walled structure, the ribs are formed by reverse extrusion, and the deformation is difficult to calculate accurately; (b) there are few positions on the forging where mechanical performance samples can be cut, and the material utilization rate is low; (c) the shape of the forging is complex , the billet needs to be completed in multiple fires, and the workload is heavy

Method used

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  • Titanium alloy smithing technological parameter testing method
  • Titanium alloy smithing technological parameter testing method
  • Titanium alloy smithing technological parameter testing method

Examples

Experimental program
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Embodiment 1

[0021] The comparative test of embodiment 1 upset cake method and the inventive method

[0022] The raw material is TC18 (Ti-5Al-5Mo-5V-1Cr-1Fe) titanium alloy φ155mm rod. First to the bar at T β Forgings in all directions at -30°C are completed in two fires, and each fire is upsetting once, and the upsetting deformation is about 50%. Forge the bar after forging to the size given in Table 1, then respectively adopt the upsetting cake method and the test method of the present invention to forge the blank. The specific process parameters of the inventive method are shown in Table 1 and the following steps:

[0023] 1) Forging titanium alloy rods in multiple fires in all directions to obtain as uniform an original structure as possible, and the low-magnification structure should conform to grades 1 to 3 in the "Titanium Alloy Low-magnification Structure 10-Grade Rating Chart";

[0024] 2) The reforged bar is made into a blank with a thickness of 100±2mm, a width of 130±2mm, and...

Embodiment 2

[0037] The raw material is TC18 titanium alloy φ170mm bar. First, the bar is forged in all directions at Tβ-40°C, and it is completed in three fires. Each fire is upset once, and the upsetting deformation is about 50%. The size of the blank after forging is 100×130×260mm. The die forging heating temperature is Tβ+25℃, and the holding time is calculated in two stages: T β -30°C, hold for 60 minutes, heat up to Tβ+25°C with the furnace, hold for 40 minutes. The test results of mechanical properties are shown in Table 3, and the corresponding relationship between deformation and mechanical properties is shown in figure 1 .

[0038] Table 3 Test results of main mechanical properties of TC18 titanium alloy forgings under different deformation

[0039]

[0040] Note: The post-forging heat treatment system is 825°C, 2h, furnace cooling to 750°C, 2h, AC+620°C, 4h, AC.

[0041] Depend onfigure 1 It can be seen that at the selected test temperature, the amount of deformation has ...

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Abstract

The invention relates to a test mode of a titanium alloy smithing technological parameter. The test mode has the steps that: (1) multi-forging various-direction smithing is performed on a titanium alloy steel bar to obtain an original structure which is as uniform as possible; (2) the steel bar after substituting forging is made into stocks under the temperature ranging from 30 to 50 DEG C below a Beta transformation point (TBeta); (3) the stocks are preheated for 1 to 2 hours under the temperature which is about 200 DEG C, and then are coated with special lubricant Ti-6 of a titanium alloy die forming; (4) the surface of a die is preheated until the temperature is more than 350 DEG C, the die forming is finished with 1 to 2 fire levels, and three different deformation amounts of 10 percent, 35 percent and 60 percent are obtained on a forgeable piece; (5) after the forgeable piece is processed through heat treatment, various types of mechanical property samples are get from the parts with different deformation amounts, and the quantitative relation between the parameters such as the smithing temperature, the heat preservation time, the deformation amounts, etc. and the mechanical property as well as microscopic constitutions is determined. A technician can adjust the sizes of the stocks according to the quantitative relation, and ensure reasonable deformation amounts on a stamp work, thereby obtaining the optimum matching between the plasticity and the fracture toughness.

Description

technical field [0001] The invention relates to a test method for a titanium alloy forging process parameter, which belongs to the technical field of metal material science. Background technique [0002] With the continuous improvement of advanced aircraft's requirements for high weight reduction and long life, the amount of titanium alloys with high specific strength and good corrosion resistance in aircraft is also increasing. Titanium alloy die forgings are mainly used to manufacture important load-bearing components such as bulkheads, beams, and engine compressor plates on aircraft, which have high requirements on the performance of forgings. Unlike aluminum alloys and structural steels, the forging process parameters of titanium alloys have a great influence on the microstructure and mechanical properties of the alloy. Taking TC6 and TC11 titanium alloys as examples, in the case of fixed chemical composition, the change of forging process can make the elongation δ fluc...

Claims

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Application Information

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IPC IPC(8): C22F1/18
Inventor 沙爱学谢静李兴无李建华王庆如熊运森储俊鹏曾菁
Owner BEIJING AVIATION MATERIAL INST NO 1 GRP CORP CHINA AVIATION IND
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