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A Bending Processing Method for Duplex Turbine Blade Locking Plate

A turbine blade and bending processing technology, applied in the aerospace field, can solve the problems of high product failure rate, high mold production cost, short mold service cycle, etc., and achieve the effect of good surface quality, stable processing and good product size

Active Publication Date: 2022-02-01
TIANJIN CHENGLI AVIATION TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Using the traditional method, the blade head is prone to large scratches and strains, the production cost of the mold is high, and the service life of the mold is short, and the product failure rate is high

Method used

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  • A Bending Processing Method for Duplex Turbine Blade Locking Plate
  • A Bending Processing Method for Duplex Turbine Blade Locking Plate
  • A Bending Processing Method for Duplex Turbine Blade Locking Plate

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Embodiment Construction

[0025] A method for bending a double-connected turbine blade locking piece, comprising the following steps:

[0026] 1) Choose two 1.5mm thick stainless steel sheets, according to the corresponding width B × length L, and mark the direction of the metal flow line, and ensure the overall length requirements; see figure 2 ;

[0027] 2) Invert the upper and lower ports of the joints of the two boards by C0.5, then carry out seam welding, and adjust the position and size of the corresponding rollers to meet the requirements;

[0028] 3) Carry out wire cutting along the direction of the metal flow line to obtain the desired length and width of the double turbine blade lock

[0029] 4) Pre-bending the head of the lock plate of the turbine blade for the fitter opening; see Figure 4 ;

[0030] 5) Based on the other end, place the processed pre-bent part in the lower mold of the bending mold, and perform final bending and forming processing on the pre-bending part of the head to r...

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Abstract

The invention provides a kind of bending processing method of double-connected turbine blade locking plate, comprising the following steps: 1) selecting two 1.5mm thick stainless steel plates; Carry out seam welding; 3) Carry out wire cutting along the direction of the metal flow line to obtain the length and width of the double turbine blade locking piece; 4) The fitter opens and processes the head of the turbine blade locking piece to pre-bend; 5) Based on the other end, place The processed pre-bent part is placed in the lower mold of the bending die, and the pre-bent part of the head is finally bent and formed to obtain the finished product. The invention adopts the processing method of bending forming through the bending forming mold, the process method is simple, the positioning of the mold is controllable, the product size is good, the appearance quality is also high, the surface quality of the bent product is good, the processing is stable and reliable, greatly It greatly saves the production cost, reduces the cost cycle of mold making, and is suitable for mass production.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a bending processing method of a double-connected turbine blade locking piece. Background technique [0002] Duplex turbine blade locking plate is a special part, which has a large number, complex shape, high requirements, difficult processing, and frequent failure parts, so its manufacturing and processing has always been the key link of various production and processing enterprises. [0003] The commonly used process for bending the existing double-connected turbine blade lock piece is: use a mold with a guide post for bending, use the mold for processing, and then weld the left and right pieces together. Using the traditional method, the blade head is prone to large scratches and strains, the production cost of the mold is high, and the service life of the mold is short, and the product failure rate is high. Contents of the invention [0004] In view of this, the present...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B21D37/10B21D7/06B23P15/02
CPCB21D37/10B21D7/06B23P15/02
Inventor 付开荣熊成红杨锦福任光瑞
Owner TIANJIN CHENGLI AVIATION TECH CO LTD
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