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Machining method for PH13-8Mo part used for aviation

A processing method and parts technology, which is applied in the field of processing PH13-8Mo parts for aviation, can solve problems such as low processing efficiency, difficult machining, and large tool wear, so as to improve efficiency, reduce heating time and energy consumption, and reduce tool wear. wear effect

Active Publication Date: 2020-01-24
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the hardness of the material after solid solution + cold treatment + artificial aging is as high as 45HRC, which is extremely difficult to machine, resulting in large tool wear and low processing efficiency

Method used

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  • Machining method for PH13-8Mo part used for aviation

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] The specific process of this embodiment, such as figure 1 shown, including the following steps:

[0033] (1) The PH13-8Mo bar is blanked, blanked, and after at least one die forging and edge trimming, a forging of a certain shape is formed, and annealed at 600~760°C to eliminate the residual stress in the forging process;

[0034] (2) Solid solution treatment of forgings;

[0035] (3) Then cold-treat the forging;

[0036] (4) After the cold treatment is completed, rough machining is carried out on the forgings to initially form blank parts;

[0037] (5) Perform artificial aging treatment on the finished blank parts;

[0038] (6) Finally, finish machining the blank parts to make finished aviation PH13-8Mo parts.

Embodiment 2

[0040] The embodiments of this city are based on the above embodiments, and are further limited in the step (1), the number of die forging is once or twice, and the number of die forging depends on the complexity of the parts, such as figure 1 As shown, during the secondary die forging, it is necessary to trim or clean the forgings of the first die forging before the second die forging can be carried out. Other parts of this embodiment are the same as those of the foregoing embodiment, and will not be repeated here.

Embodiment 3

[0042] The embodiment of this city is based on the above embodiments, and further defines that in the step (2), the solution treatment process of the forging is as follows: heating the forging to 800~1000°C, keeping it warm for 150~1800 minutes, and then heating it Raise the temperature by 5~45°C, keep it warm for 50~90 minutes, and cool to room temperature. Realize the stabilization of the solid solution of the PH13-8Mo material and avoid the precipitation of the precipitated phase. Other parts of this embodiment are the same as those of the foregoing embodiment, and will not be repeated here.

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Abstract

The invention discloses a machining method for a PH13-8Mo part used for aviation. The machining method includes the following steps that firstly, a PH13-8Mo bar is subjected to blanking and blank manufacturing and subjected to at least one time of die forging and edge cutting, a forge piece in a certain shape is formed, annealing is conducted at the temperature being 600 DEG C to 760 DEG C, and residual stress in the forging process is eliminated; secondly, the forge piece is subjected to solution treatment; thirdly, the forge piece is subjected to cold treatment; fourthly, after cold treatment is completed, the forge piece is subjected to rough machining, and a blank part is formed initially; fifthly, the manufactured blank part is subjected to manual aging treatment; and sixthly, finishmachining is conducted on the blank part, and a finished product is manufactured. By means of the machining method, a cold and heat combined technology scheme is adopted, the part is subjected to rough machining in a solid solution state, removing work of most of materials is completed under the low hardness, the cutting speed is increased, and the tool loss amount is reduced; and the equivalent thickness of the forge piece obtained after rough machining is reduced, the heating time and energy consumption of subsequent manual aging are reduced, furthermore, heat correction can be conducted onpart deformation, part of machining stress is eliminated, and part deformation is reduced.

Description

technical field [0001] The invention relates to the technical field of metal material processing, in particular to a processing method for aviation PH13-8Mo parts. Background technique [0002] PH13-8Mo (0Cr13Ni8Mo2Al) stainless steel has high strength, good fracture toughness and good transverse mechanical properties, and can have excellent stress corrosion resistance in marine and oil and gas environments. Due to the good comprehensive performance of this grade of steel, it has been widely used in the frame, beam and fuel tank with harsh working environment of the aircraft. [0003] In order to obtain the best metal streamline distribution and eliminate casting defects in raw materials, PH13-8Mo parts for aviation use PH13-8Mo forgings as raw materials for processing. In order to make PH13-8Mo meet the mechanical properties required by the standard, PH13-8Mo forgings need to undergo a series of heat treatments, the process is: solid solution - cold treatment - artificial ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C21D1/30C21D8/06C21D6/04C21D1/18B21J5/02
CPCC21D1/30C21D8/065C21D6/04C21D1/18B21J5/02C21D2261/00
Inventor 王少阳沈明张立新王力强陈丽丽
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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