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Numerical control machining method for combined matched drilling of taper holes of high-pressure turbine rotor

A technology of high-pressure turbine and processing method, which is applied in the field of numerical control processing, can solve the problem of low precision of the taper hole of the combination drill, and achieve the effect of ensuring the assembly requirements

Active Publication Date: 2017-05-31
CHINA HANGFA GUIZHOU LIYANG AVIATION POWER CO LTD
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is: to provide a numerically controlled machining method of a high-pressure turbine rotor combination drill taper hole, which is stable and reliable, and solves the problem of low precision of the combination drill taper hole

Method used

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  • Numerical control machining method for combined matched drilling of taper holes of high-pressure turbine rotor
  • Numerical control machining method for combined matched drilling of taper holes of high-pressure turbine rotor

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Embodiment Construction

[0021] Below in conjunction with accompanying drawing, the present invention is described in further detail:

[0022] Such as figure 1 As shown, the high-pressure turbine rotor of the engine is composed of three parts, of which part 1 is the sealing grate tooth disc, part 2 is the high-pressure turbine disc, and part 3 is the rear journal of the high-pressure turbine. The materials of the three parts are superalloys of different grades ; 4 is the taper hole after combination drilling, the taper of the hole is 1:50, and the depth is 61mm. Part 1, part 2 and part 3 are connected and centered by 8 taper holes 4 during the assembly process. figure 1 It can be seen that when the reamer is processed from top to bottom, the front part of the tool has the largest stroke and the most serious wear. In order to solve this problem, it is necessary to track the degree of wear of the tool during machining. The present invention establishes a feedback mechanism , which controls the processi...

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Abstract

The invention discloses a numerical control machining method for combined matched drilling of taper holes of a high-pressure turbine rotor. The numerical control machining method includes rough machining of the taper holes, finish machining and coloring and matching of taper bolts. According to the numerical machining method, the rough machining margin is controlled, abrasion changes of a taper finish reamer in the machining process are traced, the assembling requirement of parts in the machining process of combined matched drilling of the parts is ensured, and the taper and various section sizes of the taper holes are ensured by controlling the whole process of machining of the whole taper holes.

Description

technical field [0001] The invention belongs to the technical field of numerical control machining, in particular to a machining method for a combined drilling taper hole. Background technique [0002] Combined drill taper hole processing is rare in the field of mechanical processing, especially the deep taper hole processing after three parts are assembled, and the material conditions of the three parts are inconsistent, and the hole processing accuracy is also high. It is very difficult. In the manufacture of aero-engine components, there is such a processing requirement, and the precision of the tapered hole processed by the traditional method is not high, and the matching with the tapered bolt is not good, resulting in the vibration failure of the engine. At present, there is no systematic research and elaboration on the machining method of precision deep taper holes in high hardness materials in China. [0003] Such as figure 1 As shown, a certain engine part is comp...

Claims

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Application Information

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IPC IPC(8): B23P17/00
CPCB23P17/00
Inventor 杨华林
Owner CHINA HANGFA GUIZHOU LIYANG AVIATION POWER CO LTD
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