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Turbine blade sawtooth shroud wear-proof layer preparation method

A technology of turbine blades and sawtooth crowns, which is applied in the field of preparation of wear-resistant layers of turbine blade sawtooth crowns, to achieve the effects of increased service life, flexible operation, and low cost

Inactive Publication Date: 2015-03-25
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] Aiming at the problems existing in the prior art, the present invention provides a method for preparing the wear-resistant layer of the sawtooth crown of the turbine blade, which effectively reduces the point and linear fluorescent defects in the concave R area of ​​the root and the surface of the wear-resistant layer, and can reduce the primary wear-resistant layer of the turbine blade. The qualification rate of grinding layer preparation is increased to more than 90%, which minimizes the risk of cracks in the blade caused by fluorescent defects in the high stress concentration area, and effectively improves the service life of the blade

Method used

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Embodiment Construction

[0027] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0028] The turbine blade in this embodiment is a low-pressure fifth-stage working blade, and the blade material is K417G alloy.

[0029] The method for preparing a wear-resistant layer of a sawtooth crown of a turbine blade includes the following steps:

[0030] Step 1: Use the diamond forming roller to slowly grind the serrated crown position of the cast blank blade, and the feed amount of the serrated grinding process is 0.1mm; among them, the positioning tool uses the blade tenon, the blade body and the serrated crown as the positioning points. For positioning, the tolerances of the machined surfaces of the serrated crowns and their final dimensions are as follows:

[0031] ①The tolerance of the end face of the wear-resistant layer is +1.4mm~+1.6mm;

[0032] ②The tolerance of the surfacing surface of the wear-resistant layer is -0....

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Abstract

The invention provides a turbine blade sawtooth shroud wear-proof layer preparation method, and belongs to the technical field of aircraft engine part manufacturing. By means of an existing turbine blade sawtooth shroud wear-proof layer preparation method, after the machining step of creep feed grinding, a wear-proof layer is unqualified due to the fact that point and linear fluorescent defects exist in the root concave R region and the surface of the wear-proof layer, the service life of a turbine blade is directly affected due to the non-standard-exceeding fluorescent defects of the root concave R region, cracks are generated extremely easily on the high-stress concentration region due to the fluorescent defects, even chip off-falling risks exist, and the flight safety is affected seriously. By means of the turbine blade sawtooth shroud wear-proof layer preparation method, the point and linear fluorescent defects existing in the root concave R region and the surface of the wear-proof layer are overcome, the one-time preparation yield of the wear-proof layer of the turbine blade can be increased to 90%, the risk that the cracks of the blade are generated in the high-stress concentration region due to the fluorescent defects is reduced, and the service life of the blade is prolonged effectively. The turbine blade sawtooth shroud wear-proof layer preparation method has the advantages of being high in wear-proof layer bonding strength, flexible to operate, low in cost and wide in application range.

Description

technical field [0001] The invention belongs to the technical field of aero-engine parts manufacturing, in particular to a method for preparing a serrated crown wear-resistant layer of a turbine blade. Background technique [0002] The low-pressure turbine blades of aero-engines generally adopt a structure with a sawtooth crown. Each blade is connected to the turbine disk through a tenon, and cooperates with the adjacent blades through the sawtooth crown damping surface, and then is connected to form a turbine blade ring. [0003] During the operation of the aero-engine, the turbine blades will be subjected to complex torque and bending moments, which will cause extrusion and fretting wear on the damping surface of the sawtooth crown. To solve the problem of looseness, the technicians adopted the method of preparing a wear-resistant alloy layer on the blade sawtooth crown to ensure the wear resistance of the damping surface of the sawtooth crown and improve the service life ...

Claims

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Application Information

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IPC IPC(8): B23K9/04B23K9/32
CPCB23K9/044B23K9/235
Inventor 宋文清曲伸高山杨烁周冠男
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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