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Method for replacing blind hole positioning pin of low-pressure turbine disc of aero-engine

An aero-engine and low-pressure turbine technology, applied in the mechanical field, can solve problems such as sinking, inner wall damage, and hole diameter expansion, and achieve the effects of improving the processing success rate, saving production costs, and increasing chip removal force

Active Publication Date: 2019-04-09
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The depth of the positioning pin installed in the blind hole is about 5.5, and it is close to the bottom of the hole. The engine sinks during the working process. The installation depth may be close to the bottom of the blind hole during overhaul. Normal drilling is easy to damage the bottom of the blind hole.
Using the traditional drilling-tapping method, it is easy to damage the wall of the blind hole, causing the hole diameter to expand or the inner wall to be damaged, which will affect the matching data after replacement

Method used

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  • Method for replacing blind hole positioning pin of low-pressure turbine disc of aero-engine
  • Method for replacing blind hole positioning pin of low-pressure turbine disc of aero-engine
  • Method for replacing blind hole positioning pin of low-pressure turbine disc of aero-engine

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Embodiment Construction

[0020] A method for replacing a blind hole positioning pin of an aero-engine low-pressure turbine disc, comprising the following steps:

[0021] 1) Boring processing to remove the protruding part of the positioning pin 2; process parameters: equipment: TK4100 / 2, coolant: castor oil, revolution: 400r / min, feed: 0.04mm / r;

[0022] 2) The fitter makes a positioning hole on the positioning pin 2;

[0023] 3) if figure 2 As shown, use a Φ4.2 drill bit 5 to drill a hole on the positioning pin 2;

[0024] 4) if image 3 , 4 As shown, the remaining positioning pins are removed by using a Φ4.5 milling cutter 6; the milling cutter 6 is a specially-made modified milling cutter, and a 4-blade center-blade milling cutter with a small chip chamber is selected. The second relief angle and the third relief The angle of the corner is increased by 3-5° by changing the grinding; install the milling cutter 6 on the radial drill 3, the process parameters: equipment: Z3063×20 / 1, coolant: casto...

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Abstract

The invention belongs to the field of machinery, particularly relates to a method for replacing a blind hole positioning pin of a low-pressure turbine disc of an aero-engine. According to the technical scheme, the method for replacing the blind hole positioning pin of the low-pressure turbine disc of the aero-engine comprises the following steps: step one, boring machining is carried out to removethe protruding part of a positioning pin; step two, a positioning hole is formed in the positioning pin by a bench worker; step three, drilling on the positioning pin is carried out with a drill bitwith diameter of 4.2; step four, the residual positioning pin is removed by a milling cutter; step five, a blind hole of the low-pressure turbine disc is cleaned, and the new positioning pin is mounted. According to the the method for replacing the blind hole positioning pin of the low-pressure turbine disc of the aero-engine, the production efficiency is high, the success rate is high, and the production cost is saved.

Description

technical field [0001] The invention belongs to the field of machinery, and in particular relates to a method for replacing blind hole positioning pins of a low-pressure turbine disc of an aero-engine. Background technique [0002] During the overhaul of an aero-engine, it was found that 16 positioning pins on the low-pressure turbine disk had fractures and cracks to varying degrees. The low-pressure turbine disks involved in this kind of fault accounted for about 50% of the number of overhauled engines, which caused serious damage to the safety of the engine. Serious hidden dangers, so repairs must be ruled out. The replacement of the new low-pressure turbine disk assembly is used to eliminate the fault, and the purchase cost is extremely high. Cost savings can be achieved by replacing faulty positioning pins. [0003] The low-pressure turbine disk is a key part of the aero-engine, and it is subjected to large alternating stress and thermal stress during operation. The 16...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P6/04B23P15/00
CPCB23P6/045B23P15/00
Inventor 张迪王洪明刘艳良
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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