Preparation method of Ti2AlNb/TA15 bi-metal titanium alloy composite hollow structure

A hollow structure, titanium alloy technology, applied in the field of titanium alloy processing, can solve the problems of low design freedom, narrow process window, and high forming temperature, and achieve the effects of low equipment requirements, large design freedom, and low forming temperature.

Inactive Publication Date: 2018-06-15
BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of this invention is to propose a Ti 2 AlNb / TA15 Bimetallic Titanium Alloy Composite Hollow Structural Parts Preparation Method to Solve Ti 2 Poor superplasticity, low design freedom, high forming temperature, high forming pressure, and narrow process window in the preparation of AlNb alloy multilayer structure

Method used

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  • Preparation method of Ti2AlNb/TA15 bi-metal titanium alloy composite hollow structure
  • Preparation method of Ti2AlNb/TA15 bi-metal titanium alloy composite hollow structure
  • Preparation method of Ti2AlNb/TA15 bi-metal titanium alloy composite hollow structure

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Embodiment 1

[0038] The material used in this embodiment is Ti 2 AlNb alloy 5 and TA15 alloy 6.

[0039] The present invention as Figure 5 shown in the following steps:

[0040] 1. Preparation of blank

[0041] (1) Prepare the upper core board 2, the lower core board 3, the outer board 1 and the lower outer board 4 by means of wire cutting or laser cutting.

[0042] 2. Blank line drawing, surface treatment

[0043] (1) Draw lines on the upper or lower core boards 2, 3.

[0044] (2) The four-layer blank is subjected to surface treatment, and the surface treatment can be carried out by pickling or mechanical grinding to remove scale.

[0045] (3) Coat solder stop flux on the lined core board, and reserve the airflow channel t2, the width of the airflow channel t2 is about 3mm.

[0046] 3. Seal welding

[0047] (1) Assembling the surface-treated outer layer plates 1, 4 and the surface-treated core plate preform;

[0048] (2) After the four-layer slab is fixed, it is sealed by argon arc...

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Abstract

The invention provides a preparation process of a Ti2AlNb/TA15 bi-metal titanium alloy composite hollow structure part. The Ti2AlNb/TA15 bi-metal titanium alloy composite hollow structure wing type component is prepared through the steps of blank preparation, surface treatment, welding stop agent coating, superplastic forming/diffusion bonding, cooling, out of a furnace and the like. The superplastic forming/diffusion bonding process method of the dissimilar material hollow structure part breaks through the key technology of the multi-layer hollow structure prepared by combining a Ti2AlNb intermetallic compound and an ordinary titanium alloy, the high-temperature resisting characteristic of the Ti2AlNb intermetallic compound and the good superplasticity of the TA15 titanium alloy are givento full play, structure weight losing is achieved, the guided missile thrust-weight ratio is increased, the application of the Ti2AlNb intermetallic compound to types is promoted, the material application range is expanded, the material utilization rate is increased, and the cost is reduced.

Description

technical field [0001] The invention belongs to the technical field of titanium alloy processing, in particular to a Ti 2 A preparation method of AlNb / TA15 bimetallic titanium alloy composite hollow structure. Background technique [0002] Ballistic-cruise combined missile (referred to as combined missile) is a new generation of long-range precision strike new concept missile weapon system in my country. Ballistic-cruise combined missile organically integrates ballistic missile and cruise missile technology. It adopts a new ballistic trajectory of "boost-unpowered gliding-powered cruise" to achieve long-range precision strikes. The first half of the flight of the combined missile is an inertial parabolic trajectory, which has the characteristics of inertial flight outside the atmosphere of the ballistic missile; in the second half of the trajectory, the missile re-enters the maneuvering cruise flight in the atmosphere, which has the characteristics of a cruise missile. [...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/00B23K9/173B23K9/23
CPCB23P15/00B23K9/173B23K9/232
Inventor 王斌刘岭马向宇刘太盈刘章光高海涛
Owner BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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