Manufacturing method for dissimilar alloy integral blade disc structure

Abstract

The invention relates to a manufacturing method for a dissimilar alloy integral blade disc structure. The method comprises the steps that a blade disc is rotationally and axially mounted on a high-conductivity metal support base through a high-conductivity metal support shaft, and the support base is mounted on a graphite electrode bottom plate; and after blades and the blade disc are assembled, discharge plasma diffusion welding is adopted for welding, during welding, the upper portions of the blades are pressed through a graphite electrode pressing block, direct current pulse current is connected between the graphite electrode pressing block and the graphite electrode bottom plate, discharge plasma is generated, diffusion welding of the blades and the blade disc is rapidly achieved underthe action of impact pressure, joule heat and an electric field, all the blades are welded to the blade disc, and the integral blade disc is obtained, wherein the blades and the blade disc are prepared from different alloys. Through the discharge plasma diffusion welding method, the problems of high manufacturing difficulty and high scrap rate of integral blade discs are solved, the performance and economic complementarity advantages of the dissimilar alloys are fully achieved, and the demand for the high performance integral blade disc of aeroengines is met.

Description

Technical field [0001] The invention relates to the technical field of aviation manufacturing, in particular to a method for manufacturing a dissimilar alloy integral blisk structure. Background technique [0002] In the field of aviation manufacturing technology, currently, the manufacturing methods of blisks mainly include mechanical processing, fusion welding, linear friction welding, and hot-pressure diffusion welding. However, these manufacturing methods have certain shortcomings and limitations, as follows: [0003] (1) The overall mechanical processing increases the size and weight of the blank material for forgings. The material utilization rate is low, the processing is difficult, the product qualification rate is low, and the production cost is high. It is only suitable for manufacturing blisks of the same material. [0004] (3) The joint structure of fusion welding is a cast structure, which is prone to shortcomings such as porosity, slag inclusion, unwelded, coarse struct...

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Problems solved by technology

[0003] (1) The overall mechanical processing increases the size and weight of the forging blank material, the material utilization rate is low, the processing is difficult, the product qualification rate is low, and the production cost is high, and it is only suitable for manufacturing the overall blisk of the same material

[0004] (3) The joint structure of fusion welding is cast structure, which is prone to defects such as pores, slag inclusions, unwelded, and coarse structure. The joint performance and structure consistency are poor, resulting in low joint reliability and low product qualification rate.

[0005] (4) Linear friction welding is not suitable for manufacturing integral blisks with cooling channels because the welded parts are subjected to a large upsetting force and require high strength and hardness.

[0006] (5) Hot-pressed diffusion welding can prepare complex-structure blisks, but it is heated as a whole. When preparing heterogeneous blisks, it is difficult to take into account the matching welding process of the two materials at the same time. The welding time is long and the base material Large performance loss

[0007] With the continuous improvement of aviation weapon equipment performance requirements, more and more new materials and new structures are used, which put forward higher requirements for aviation manufacturing technology including welding technology. The manufacturing methods of the above-mentioned existing technologies meet Unable to meet the manufacturing requirements of high-performance engine blisks

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