Powder-solid coupling forming device and method for plurality of layers of ribs in interior of thin-wall part

Abstract

The invention discloses a powder-solid coupling forming device for a plurality of layers of ribs in the interior of a thin-wall part. The powder-solid coupling forming device comprises a container, a rib plate and a mold core are arranged in the container, the container comprises a top plate, a wrapping sleeve and a bottom plate, the wrapping sleeve is in a barrel shape with the top end and the bottom end open, the top end of the wrapping sleeve is connected with the top plate in a sealed mode, the bottom end of the wrapping sleeve is connected with the bottom plate in a sealed mode, the mold core is used for supporting the rib plate, a forming cavity is formed between the mold core and the wrapping sleeve, and a through hole communicating with the forming cavity is further formed in the top plate. A powder-solid coupling forming method for the plurality of layers of ribs in the interior of the thin-wall part comprises the steps that the container, the rib plate and the mold core are prepared, after powder is added into the forming cavity, heating and vacuumizing are carried out on the whole container, then the container is put into a hot isostatic pressing furnace for forming in the high-temperature and high-pressure environment, and finally the container and the mold core are removed. According to the device and the method, integral forming of the high-performance thin-wall structure with the ribs can be achieved.

Description

technical field [0001] The invention relates to the technical field of aviation equipment manufacturing, in particular to a powder-solid coupling forming device and method for multi-layer ribs and ribs inside a thin-walled part. Background technique [0002] The development of aerospace technology has put forward an increasingly strong demand for complex thin-walled powder structures. In terms of design, in order to meet the harsh service environment requirements and reduce the weight of the aircraft as much as possible, titanium alloys, aluminum alloys, magnesium alloys, etc. demanding. In terms of preparation, it is difficult to meet the requirements of molding process, service performance and cost reduction by conventional casting and forging methods for large-scale thin-walled structures. Therefore, how to integrally form high-performance ribbed thin-walled structures has become a key technical issue. [0003] At present, thin-walled parts with ribs are mainly made of...

AI Technical Summary

Problems solved by technology

[0003] At present, thin-walled parts with ribs are mainly made of high-quality alloys through forging deformation, machining, and then connected by electron beam welding. The process of machining or free forging will lead to a lot of waste of materials and hypertrophy of components. , it is difficult to meet the requirements for light weight in aviation components. Welding leads to large deformation and out-of-tolerance upper and lower profiles, which cannot meet the connection and installation. Moreover, the fatigue resistance is poor, and the ideal mechanical properties cannot be achieved, so it is difficult to meet the requirements of aircraft use.

In addition, the method of casting can also be used, but when large thin-walled structural parts are cast, interface reactions between the casting and the mold are prone to occur, and at the same time, many common casting defects will appear, including pores, shrinkage cavities (shrinkage porosity) ), inclusions, cracks, sticky sand, burrs, cold sun (wandering), fire escape, insufficient pouring and segregation and other internal and surface quality problems

The existence of these defects weakens the mechanical properties of the material and limits the application of titanium alloy components in the new generation of aerospace vehicles.

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