Laser processing method for air film holes of high-pressure turbine guiding blade

A laser processing method and turbine guide vane technology, applied in laser welding equipment, metal processing equipment, manufacturing tools, etc., can solve the problems of damage to the inner cavity and poor consistency of parts, so as to improve the surface integrity and ensure the position The effect of reducing the error

Active Publication Date: 2019-01-08
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since it is a cast part, the surface consistency of the part is poor, and there is a problem of damage to the inner cavity during the process of laser processing the gas film hole

Method used

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  • Laser processing method for air film holes of high-pressure turbine guiding blade
  • Laser processing method for air film holes of high-pressure turbine guiding blade
  • Laser processing method for air film holes of high-pressure turbine guiding blade

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Embodiment Construction

[0030] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0031] Analysis of the influence of the leaf profile on the air film hole position: as Figure 4 As shown, Ⅰ-Ⅰ, Ⅱ-Ⅱ, Ⅲ-Ⅲ represent the theoretical profile position, profile thickening position and profile thinning position of the turbine blade respectively. The laser beams J, K, L are parallel light. When the laser beam J irradiates the turbine blade profiles Ⅰ-Ⅰ, Ⅱ-Ⅱ, Ⅲ-Ⅲ, they will intersect at points O, O 3 , O 4 . Relative to the theoretical intersection point O, the intersection point O 3 and O 4 The position tolerance between the theoretical intersection point O is the radius R of the circle. It is manifested on the part, that is, when the profile of the turbine blade is thickened to the profile II-II, the intersection point of the air film hole and the profile surface of the part moves from the theoretical point O to the intersec...

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Abstract

The invention discloses a laser processing method for air film holes of a high-pressure turbine guide blade, and belongs to the field of aviation engine manufacturing. Through a method of automatic programming combined with manual animation teaching programming, the surface of a part is dotted using a theoretical coordinate value, teaching and recording back of a processing program is completed through manual animation, the influence of the casting surface difference of the turbine blade and rotating shaft motion errors of a machine tool on the air film hole location is reduced, and the location degrees of the air film holes of the high-pressure turbine hollow blade are guaranteed.

Description

technical field [0001] The invention belongs to the technical field of aero-engine manufacturing, and in particular relates to a laser processing method for a gas film hole of a guide blade of a high-pressure turbine. Background technique [0002] The turbine is the part with the largest thermal load and mechanical load in the aero-engine. The working environment of the turbine blade is particularly harsh. In the engine cycle, it bears the impact of high-temperature and high-pressure gas after combustion. Its manufacturing technology is listed as the key technology of modern aero-engines . Turbine blade film hole cooling technology is a feasible and efficient way to increase the turbine inlet temperature and ensure the reliable operation of turbine blades in high temperature environment. The main structural feature of the air film cooling technology is that n rows of cooling air film holes are distributed along the direction of the blade shape on the turbine blade body, and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23K26/382B23K26/08B23K26/142
CPCB23K26/0884B23K26/142B23K26/382
Inventor 王辉明张文才朱红钢阮成勇耿军儒李文涛魏颖张超
Owner AECC AVIATION POWER CO LTD
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