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Titanium alloy double layer curved surface wing plate part heat treatment deformation control method

A double-layer curved surface, titanium alloy technology, applied in the field of heat treatment of aircraft parts, can solve the problems of thermal expansion and contraction, cold and hot deformation, etc., to achieve the effects of improving efficiency, saving costs, and being convenient to manufacture and use

Active Publication Date: 2014-12-17
XI'AN AIRCRAFT INTERNATIONAL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This kind of tooling is different from ordinary machining equipment. It has to work repeatedly in the hot and cold cycle of high temperature heating and cooling, which will cause thermal expansion and contraction, and it will also face the problem of thermal deformation.

Method used

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  • Titanium alloy double layer curved surface wing plate part heat treatment deformation control method
  • Titanium alloy double layer curved surface wing plate part heat treatment deformation control method
  • Titanium alloy double layer curved surface wing plate part heat treatment deformation control method

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Embodiment Construction

[0018] Referring to the accompanying drawings, the part 1 in the embodiment is a titanium alloy double-layer curved wing plate part in a certain type of aircraft, and the material of the part is a Ti-6Al-4V free forging. like figure 1 As shown, the part is about 1 meter long, the wall thickness and rib thickness are 5mm, and this part is different from the general edge part. The general edge part has vertical ribs on one curved surface, while this part is on the upper and lower curved surfaces. There are vertical tendons. The surface of the part that needs to control the deformation, including the upper and lower surfaces of the lower wing and the lower surface of the lower wing, are all precision surfaces, and the design theoretical shape data of the part is known.

[0019] In order to control the deformation of the part during heat treatment, the present invention discloses such as image 3 In the shown control method, at first there must be a deformation control fixture, ...

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Abstract

The invention relates to a titanium alloy double layer curved surface long-edge strip part heat treatment deformation control method. The above part is composed of a thin-wall curved surface-shaped upper layer wing plate, a lower layer wing plate and a raised rib penetrating the center of the double layer curved surface wing plate, the part also comprises a deformation control jig, the jig contains a jig body, positioning platforms fixed on the jig body, a compacting block and an upper layer wing plate supporting and positioning plate, the part is placed on the upper surfaces of the positioning platforms, the raised rib of the part is embedded into a raised rib avoiding groove between the positioning platforms, and the part is separated from the deformation control jig after the deformation control jig and the part are subjected to heat treatment.

Description

technical field [0001] The application belongs to the field of heat treatment of aircraft parts, and relates to a method for controlling heat treatment deformation of aircraft titanium alloy double-layer curved wing plate parts. Background technique [0002] In aircraft manufacturing, there are many double-layer curved wing-like machined parts. Most of these parts are Ti-6Al-4V forgings in the raw material state, and their structure is thin. ribs. With the continuous development of aircraft technology, in some large aircraft, these double-layer curved wing plate parts are longer in length, complex in shape, large in curvature change and thin in wall. The theoretical outer surface and vertical rib surface of these double-layer curved wing plate parts need to be processed by multiple CNC machining, which are CNC rough milling, semi-finish milling, and fine milling. [0003] In the machining production of titanium alloy double-layer curved wing plate machining parts, great in...

Claims

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Application Information

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IPC IPC(8): C22F1/18
Inventor 史春玲王建峰王浩军田有安
Owner XI'AN AIRCRAFT INTERNATIONAL
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