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A processing method for arc tooth tenon blade of aero-engine compressor

A technology for aero-engines and compressors, which is applied in the field of improving the processing method of aero-engine arc tooth tenon blades, and can solve the problems of low processing efficiency, poor consistency of combined turning arc tooth tenon, and combined turning arc tooth tenon debugging period. Long and other problems, to achieve high processing efficiency, shorten the processing cycle, ensure the effect of contour and surface quality

Active Publication Date: 2017-11-28
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The main disadvantages of this processing method are: 1) The profile tolerance requirements of the tenon head are relatively strict, the consistency of the circular arc tooth tenon head processed by combined turning is poor, it is difficult to guarantee the tenon head profile tolerance, the tool marks left after turning are more obvious, and the tenon head The quality of the machined surface is poor; 2) The commissioning cycle of the combined turning arc tooth tenon is long and the processing efficiency is low

Method used

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  • A processing method for arc tooth tenon blade of aero-engine compressor
  • A processing method for arc tooth tenon blade of aero-engine compressor
  • A processing method for arc tooth tenon blade of aero-engine compressor

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Embodiment

[0026] The arc-tooth tenon blade blank is precision forging, and its structure is as follows: figure 1 Shown, blank structure see figure 2 , Tenon 1 has machining allowance, blade body 3 and inner edge plate 7 have no allowance, intake side 4 and exhaust side 6 have machining allowance, tenon 1 is connected with process boss 8, blade tip 5 is connected with process boss 9 connected. Its processing steps are:

[0027] (1) Milling and exhaust edge: On the CNC milling machine, the process boss 8 and the process boss 9 are positioned and clamped for rough milling the inlet edge 4 and the exhaust edge 6, which are used as step (2) low melting point positioning alloy pouring benchmark.

[0028] (2) Low-melting point positioning alloy pouring: the blade is clamped in the positioning pouring fixture, and the positioning pouring fixture is positioned with the blade body 3, the air inlet edge 4 and the inner edge plate 7, and the low melting point positioning alloy block is a cuboid...

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Abstract

The invention belongs to the processing technology of aero-engine compressor blades. The invention provides a method for processing an aero-engine compressor arc-tooth tenon blade, which includes: clamping the blade wool material with a root process boss and a blade tip process boss in a numerical control On the milling machine, carry out rough milling on the air inlet and exhaust sides of the blade; clamp the blade after rough milling in the positioning casting fixture, and pour the blade with low melting point alloy, and the shape of the blade after casting is a cuboid; CNC milling machine Clamp the poured cuboid blade, rough mill the tenon and edge plate at the root of the blade, and remove the technological boss at the root of the blade; finely grind the tenon into an arc tooth shape on the six-axis slow-feed grinding center; place the cuboid blade on the Put it into the melting furnace, heat it to 180°C, and take out the blade after the low-melting point alloy is melted; use the tenon to position and clamp, and finely grind the intake side and exhaust side on the CNC abrasive belt grinder; The blade tip is processed on the machine tool, and the process boss is removed.

Description

technical field [0001] The invention belongs to the processing technology of aero-engine compressor blades, and relates to the improvement of the processing method of aero-engine arc-tooth tenon blades. Background technique [0002] For a certain type of engine compressor, a kind of arc-tooth tenon blade structure, see figure 1 , The blade is composed of tenon 1, edge plate 2, blade body 3 and blade tip 5. The tenon 1 is a radial arc dovetail structure, the tenon 1 is connected to the edge plate 2 , and the edge plate 2 is connected to the blade body 3 . At present, the main steps of domestic processing of radial arc dovetail tenon blades are: use precision forging blanks, first process the inlet and exhaust edges, and then use low melting point positioning alloy package casting, then combine turning to process the tenon, and milling to process the blade tip , and finally melt the low melting point positioning alloy. The main disadvantages of this processing method are: 1...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P15/02
Inventor 马辉张婵冯全全赵赟张新东
Owner AECC AVIATION POWER CO LTD
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