Shape Correction Method for Deformation of Titanium Alloy Frame Parts

A technology for titanium alloys and parts, which is applied in the field of deformation correction of titanium alloy frame parts, which can solve the problems of unusable, limited equipment correction capability, long cycle, etc., and achieve the effect of short correction cycle and low correction cost

Active Publication Date: 2020-04-24
SHENYANG AIRCRAFT CORP
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, titanium alloy materials are highly sensitive to stress concentration, and traditional cold calibration methods (manual calibration, hydraulic calibration) cannot be used for such parts
The process of the thermal shaping method is complicated, and the shaping effect cannot be grasped in real time. It is necessary to repeat the shaping of the parts, and the cycle is long
At the same time, the shape correction capability of the equipment is limited by the external dimensions of the parts

Method used

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  • Shape Correction Method for Deformation of Titanium Alloy Frame Parts
  • Shape Correction Method for Deformation of Titanium Alloy Frame Parts

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Embodiment Construction

[0030] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0031] Such as figure 1 As shown, the part is a C-shaped frame part, which is used to connect the rear bucket section and tail cone of the aircraft. The drawing requires that the flatness of the web surface be ±0.25mm. The parts were twisted and deformed after sand blasting, which made the rear barrel section unable to connect with the tail vertebrae. See the part structure and shape correction parts figure 1 , the relative position and direction of the nozzle and the part see figure 2 .

[0032] The method for correcting the deformation of the titanium alloy frame type parts has the following steps:

[0033] The first step: put the web surface of the part on the platform, and add a force of 2.5 kg at an interval of 300 mm.

[0034] Step 2: Use a feeler gauge to measure the gap between the web surface of the part and the platform. The ga...

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Abstract

The invention belongs to the technical field of machining, and relates to a method for correcting shape in case of deformation of a titanium alloy frame-kind part. The method comprises the following steps that a skin part is placed on the surface of a milling tool; a web surface of the part is placed on a detection platform, and force of 2.5 kilograms is exerted at intervals of 300 mm; the gap between the web surface of the part and the platform is measured by a feeler gauge, and then the part undergoes shot blasting by adopting air pressure of 10-25 PSI and a coverage rate of 40-60% for shapecorrection; the flatness of the part is detected again, the shape is repeatedly corrected until the flatness of the web surface of the part is less than + / -0.25 mm. According to the method, no damageis caused to the surface of the part, no adverse effect is made on the part performance, the shape correcting method and parameters can be routined and combined on a process file to be used for guiding different operators, the shape correcting period is short, the shape correcting effect can be known in real time, the shape correcting capability is not affected by the appearance size of the part,a special fixture is not needed, and the shape correcting cost of the method is lower than that of thermal shape correcting.

Description

technical field [0001] The invention belongs to the technical field of mechanical processing, and relates to a shape correction method for deformation of titanium alloy frame parts. Background technique [0002] Titanium alloy frame parts are one of the most important load-bearing components in an aircraft and are the assembly skeleton of the aircraft. Drawings have very high requirements on the flatness of this type of parts, and the parts are easy to go out of tolerance after processing. However, titanium alloy materials are highly sensitive to stress concentration, and traditional cold calibration methods (manual calibration and hydraulic calibration) cannot be used for such parts. The process of the thermal shaping method is complicated, and the shaping effect cannot be grasped in real time. It needs repeated shaping of the parts, and the cycle is long. At the same time, the shape correction capability of the equipment is limited by the external dimensions of the parts...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B21D3/00B21D53/92
CPCB21D3/00B21D53/92
Inventor 马丽滨张兆龙焦玉坤
Owner SHENYANG AIRCRAFT CORP
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