Turbine rotor blade tenon tooth laser shock processing method

A laser shock strengthening and turbine rotor technology, applied in the aviation field, can solve the problems of short service life and crack fracture, and achieve the effect of avoiding fatigue fracture, prolonging service life and improving fatigue performance.

Active Publication Date: 2015-10-07
CHINA HANGFA SOUTH IND CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides a laser shock strengthening method for tenon teeth of turbine rotor blades to solve the techni...

Method used

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  • Turbine rotor blade tenon tooth laser shock processing method
  • Turbine rotor blade tenon tooth laser shock processing method
  • Turbine rotor blade tenon tooth laser shock processing method

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0044] 1) Inspect and clean the turbine blades that need to be strengthened;

[0045] 2) The laser enters the preparation stage, adjust the corresponding parameters in the laser, the laser shock strengthening parameters are: laser wavelength 1064nm, laser pulse frequency 1Hz, laser pulse waveform width 22nm, focus spot size before laser projection ∮3.2mm. On the corresponding area of ​​the surface of the blade to be treated, water is used to form a constrained layer, the thickness of the formed constrained layer is 5 mm, and the water pressure is 0.04 MPa. Laser power density 7.96GW / cm 2 , the overlap rate is 100%.

[0046] 3) Paste the absorbing protective layer on the surface of the blade to be treated, and use aluminum foil as the absorbing protective layer;

[0047] 4) The blade is clamped on the laser, and the position to be treated is positioned, and then impact strengthening is performed on the blade according to the above conditions. During processing, the laser ene...

Embodiment 2

[0051] 1) Inspect and clean the turbine blades that need to be strengthened;

[0052] 2) The laser enters the preparation stage, adjust the corresponding parameters in the laser, the laser shock strengthening parameters are: laser wavelength 1064nm, laser pulse frequency 1Hz, laser pulse waveform width 18nm, focus spot size before laser projection ∮ 2.8mm. On the corresponding area of ​​the surface of the blade to be treated, water is used to form a constrained layer, the thickness of the formed constrained layer is 0.5 mm, and the water pressure is 0.04 MPa. Laser power density 3.3GW / cm 2 , The overlapping rate is 65%.

[0053] 3) paste the absorbing protective layer on the surface of the blade to be treated, and use black paint as the absorbing protective layer;

[0054] 4) The blade is clamped on the laser, and the position to be treated is positioned, and then impact strengthening is performed on the blade according to the above conditions. During processing, the laser ...

Embodiment 3

[0058] 1) Inspect and clean the turbine blades that need to be strengthened;

[0059] 2) The laser enters the preparation stage, and adjusts the corresponding parameters in the laser. The laser shock strengthening parameters are: laser wavelength 1064nm, laser pulse frequency 1Hz, laser pulse waveform width 20nm, laser focus spot size ∮3mm before projection. On the corresponding area of ​​the surface of the blade to be treated, water is used to form a constrained layer, the thickness of the formed constrained layer is 1 mm, and the water pressure is 0.04 MPa. Laser power density 4.3GW / cm 2 , the overlap rate is 100%.

[0060] 3) paste the absorbing protective layer on the surface of the blade to be treated, and use the adhesive tape as the absorbing protective layer;

[0061] 4) The blade is clamped on the laser, and the position to be treated is positioned, and then impact strengthening is performed on the blade according to the above conditions. During processing, the las...

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Abstract

The invention provides a turbine rotor blade tenon tooth laser shock processing method. A turbine rotor blade comprises a blade portion and a cylinder portion connected to the bottom of the blade portion, one side of the cylinder portion is provided with a tenon tooth portion, the connection of the tenon tooth portion and the cylinder portion is an R area, laser shock processing is carried out on the R area and the tenon tooth portion close to the R area, and laser shock processing conditions comprise a laser power density of 3.3-7.96GW/cm<2> and an overlapping rate of 65-100%. The method allows the roughness, hardness, residual stress and the microstructure of the surface of a processed member to be optimized through adjusting the laser shock processing method, the laser power density and the overlapping rate, effectively improves the fatigue performance of the blade at 530DEG C, prolongs the service life, and avoids the frequent generation of fatigue fracture.

Description

technical field [0001] The invention relates to the aviation field, in particular to a method for laser shock strengthening of tenon teeth of a turbine rotor blade. Background technique [0002] Laser shock peening (LSP), also known as laser peening, is a new type of material surface strengthening technology, which uses the shock wave mechanical effect induced by strong laser to process materials, with high pressure, high energy, ultrafast and ultrahigh strain rate, etc. features. The residual compressive stress layer formed by it can effectively eliminate the stress concentration inside the material and inhibit the initiation and expansion of cracks, and can significantly improve the fatigue life, corrosion resistance and wear resistance of metal parts. A large number of studies have proved that laser shock strengthening technology is an effective means to prolong the crack initiation time, reduce the crack growth rate and improve the material life. However, in the prior ...

Claims

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Application Information

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IPC IPC(8): C21D10/00
Inventor 杨春华倪慧妍何卫锋刘昌华
Owner CHINA HANGFA SOUTH IND CO LTD
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