A limit device and clamping method for heat treatment of a double-layer structure welded assembly

Abstract

The present invention discloses a limited device and clamping method for the heat treatment of double -layer structure welding composition. The limit device includes the outer disk, inner plate, chassis, attentive shaft, and pressure plate.The disk, and the three are assembled on the heart axis.The outer surface of the outer disk is a first ring -shaped outer cylinder, and the inner surface of the inner surface of the outer structure of the first ring -shaped outer cylinder and the double -layer structure welding is tight;The outer surface of the inner structure of the inner structure of the second ring -shaped outer cylinder and the double -layer structure welding is tight; the upper end of the chassis is set with a pressure plate connected by the first bolt, and the outer installation edges of the outer layer of the double -layer structure welding component areThe inner layer is installed between the upper end of the pressure plate and the upper end of the chassis.The restriction device of the present invention is used for the installation of the installation of the inner and outer layers of the inner and outer layers of the inner and outer layers of the inner and outer layers.A pre -school volume to ensure assembly requirements.

Description

technical field [0001] The invention belongs to the technical field of thermal processing, and relates to a limiting device and a clamping method for heat treatment of a double-layer structure welding assembly. Background technique [0002] Such as figure 1 As shown, in the assembly process of aero-engine components, welding of a double-layer structure assembly is involved. After welding and heat treatment, the inner and outer rings are deformed greatly, and the workload of post-machining correction is very large. During the processing, it is reflected that the part affects the processing progress. When turning the inner and outer mounting edges of the part, the deformation of the part will be large, the concentricity of the inner and outer mounting edges will be poor, the calibration workload will be large, and the turning process will cut into the main body of the part. Because there is no supporting special tooling for the heat treatment of the part, the welding stress h...

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Problems solved by technology

[0002] like figure 1 As shown, in the assembly process of aero-engine components, it involves the welding of a double-layer structure assembly. After welding and heat treatment, the deformation of the inner and outer rings is large, and the post-machining correction workload is very large. During the processing, it is reflected that the part affects the processing progress.

When turning the inner and outer mounting edges of the part, the deformation of the part will be large, the concentricity of the inner and outer mounting edges will be poor, the calibration workload will be large, and the turning process will cut into the main body of the part, etc.

Because there is no matching special tooling for the heat treatment of this part, the welding stress heat treatment is carried out in a free state, resulting in large deformation of the part after heat treatment, poor concentricity of the inner and outer layer mounting edges, and uneven gap at the exit of the big head, which increases the heavy calibration workload of subsequent turning processing

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