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High-temperature alloy large-diameter thin-wall pyramidal integral casing machining method

A technology of high-temperature alloys and processing methods, which can be used in mechanical equipment, engine components, machines/engines, etc., and can solve problems such as deformation of parts

Inactive Publication Date: 2015-04-01
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology

[0007] Aiming at the shortcomings of the prior art, the present invention proposes a processing method for a high-temperature alloy large-diameter thin-walled cone integral casing to solve the problem of deformation of high-temperature alloy large-diameter thin-walled cone integral casing parts. At the same time, the purpose of improving quality, processing efficiency and reducing costs

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  • High-temperature alloy large-diameter thin-wall pyramidal integral casing machining method

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Embodiment Construction

[0037] An embodiment of the present invention will be further described below in conjunction with the accompanying drawings.

[0038] In the embodiment of the present invention, according to the experience of the existing processing technology, the effective method to solve the excessive deformation of the parts after welding is to adjust the margin of the single part and the assembly, and leave all the final dimensions except the casing outside. Process the welded assembly, so that the deformation caused by welding can be removed in the processing of the assembly to ensure the size requirements.

[0039] In the embodiment of the present invention, the low-pressure turbine casing is processed, and the low-pressure turbine casing such as figure 1 As shown, the processing flow chart is as follows figure 2 shown, including the following steps:

[0040] Step 1. Install the high-temperature alloy large-diameter thin-walled cone overall casing wool on the machine tool and rough p...

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Abstract

The invention discloses a high-temperature alloy large-diameter thin-wall pyramidal integral casing machining method and belongs to the machine manufacturing field. The machining method changes a former machining mode that an internal profile and an external profile are machined in different procedures, the remaining is not uniform in distribution, and the size is difficult to guarantee, guarantees parts being delivered in a qualified mode and a knife connecting requirement between a single part and an assembly and finally forms into a technological process with three-time lathing of the single part, one-time lathing of the assembly and boring machining. According to the high-temperature alloy large-diameter thin-wall pyramidal integral casing machining method, the factor that a thin-wall casing is easy to deform and the parts are avoided from vibrating through different auxiliary bearing modes in finish turning and hole boring; selection of finish turning tools, a moving path and parameters are optimized; high-temperature alloy small-diameter threaded hole manual tapping is replaced by the screw thread milling machining technology; the size accuracy of parts is guaranteed, high quality and efficiency and low costs are achieved, and the market application prospect is wide.

Description

technical field [0001] The invention belongs to the field of mechanical manufacturing, and in particular relates to a processing method for a high-temperature alloy large-diameter thin-wall cone integral casing. Background technique [0002] With the rapid development of my country's aviation industry, the technology of large-scale transport aircraft has been continuously improved, and the technology of large-scale transport engines has also been continuously improved, and the requirements for parts are also getting higher and higher; large-diameter casing parts are widely used in large-scale transport engines. , as a typical thin-walled cone integral casing of casing parts, this type of casing is characterized by complex structure, high dimensional accuracy, thin wall, and difficult processing of materials; [0003] The low-pressure turbine casing unit is composed of three parts: the low-pressure turbine shaft assembly, the low-pressure turbine stator assembly and the low-pr...

Claims

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Application Information

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IPC IPC(8): B23P15/00
CPCB23P15/00F01D25/00F05D2230/10
Inventor 苗鸿志尚小丽闻男
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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