Bending machining 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 mold production cost, high product failure rate, short mold service cycle, etc., and achieve the effect of stable processing, good surface quality and good product size

Active Publication Date: 2020-05-15
TIANJIN CHENGLI AVIATION TECH CO LTD
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  • Abstract
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  • 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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  • Bending machining method for duplex turbine blade locking plate
  • Bending machining method for duplex turbine blade locking plate
  • Bending machining method for duplex turbine blade locking plate

Examples

Experimental program
Comparison scheme
Effect test

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 bending machining method for a duplex turbine blade locking plate. The bending machining method comprises the following steps of (1), selecting two stainless steel plates withthe thickness being 1.5 mm; (2), chamfering C0.5 into the upper and lower ports of the joint of the two plates, and then carrying out roll welding; (3), carrying out linear cutting machining in the metal streamline direction to obtain the length and the width of the duplex turbine blade locking plate; (4), pre-bending the head of the turbine blade locking plate through opening machining by a bench worker; and (5), taking the other end as a benchmark, placing the machined pre-bent part in a lower die of a bending die, and carrying out final bending forming machining on the pre-bent part of thehead to obtain a finished product. According to the method, a bending forming die and a bending forming machining process method are adopted, the process method is simple, die positioning is controllable, the product size is good, the appearance quality is high, the surface quality of a bent product is good, machining is stable and reliable, the production cost is greatly saved, the die manufacturing cost period is shortened, and the bending forming die is suitable for large-batch 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 Applications(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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