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A method for repairing the side wall of a single crystal superalloy turbine blade

A technology of turbine blades and high-temperature alloys, applied in the field of high-temperature alloys, can solve problems such as difficult to complete the repair of blade side walls, achieve the effects of improving stability, reducing the number of miscellaneous crystals, and preventing blade deformation

Active Publication Date: 2022-06-17
北京煜鼎增材制造研究院股份有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, the current laser additive repair of single crystal superalloy turbine blades is mainly used for the extension repair of the blade tip and partial repair of the blade root, and it is difficult to complete the repair of the blade side wall by conventional repair methods

Method used

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  • A method for repairing the side wall of a single crystal superalloy turbine blade
  • A method for repairing the side wall of a single crystal superalloy turbine blade
  • A method for repairing the side wall of a single crystal superalloy turbine blade

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Effect test

Embodiment 1

[0040] There are shallow crack defects on the sidewall of the second-generation single crystal high-pressure turbine blade after service. After grinding the defect area, the following process parameters are used to repair it. The laser power is 600W, the scanning speed is 300mm / min, and the powder feeding amount is 8.5g / min. , the spot diameter is 2mm, that is, the energy input E per unit area is 60 J mm -2 , the repair powder is spherical DD5 powder with a diameter of 55-72 μm, and the stress relief treatment at 600 °C × 5h is carried out immediately after the repair.

[0041] figure 2 For the microstructure of the repaired area, there are no defects such as holes and cracks in the repaired area, the bottom is epitaxially grown single crystal, and the top has miscellaneous crystals. After the repair, the top miscellaneous crystal area can be removed by machining.

[0042] In summary, the present invention provides a feasible method for repairing the sidewall of a single cry...

Embodiment 2

[0044] There are shallow wear defects on the sidewall of the second-generation single crystal high-pressure turbine blade after service. After grinding the defect area, the following process parameters are used to repair it. The laser power is 600W, the scanning speed is 300mm / min, and the powder feeding amount is 8.5g / min. , the spot diameter is 2mm, and the overlap rate is 50%. The repair powder is spherical DD5 powder with a diameter of 55-72μm. Immediately after the repair, a stress relief treatment of 600 ° C × 5h is performed.

[0045] image 3 The microstructure diagram of the repaired area shows that there are no defects such as holes and cracks in the repaired area, and the bottom is an epitaxially grown single crystal.

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Abstract

The invention discloses a method for repairing the side wall of a single crystal superalloy turbine blade, comprising the following steps: 1) judging whether to repair according to the defects of the turbine blade to be repaired, specifically judging that if the depth of the defect is 50% of the thickness of the side wall Above, or if the defect is near the gas film hole, give up the repair; otherwise, prepare for repair; 2) Carry out pre-treatment according to the specific situation of the defect; The laser additive repair is carried out by means of shaft feeding. During the repair process, the turntable is turned to adjust the position of the turbine blade to be repaired, so as to ensure that the angle between the incident laser line and the normal line of the turbine blade surface is less than 15°; 4) The laser additive repair The finished turbine blades are immediately put into a heat treatment furnace for heat treatment to remove thermal stress. The method of the invention is practicable, can prolong the service life of blades, and reduce the manufacturing and maintenance costs of the engine.

Description

technical field [0001] The invention relates to the technical field of superalloys, in particular to a method for repairing the sidewalls of single-crystal superalloy turbine blades. Background technique [0002] At present, the shape and manufacturing process of single-crystal hollow turbine blades of aero-engine are complex. Defects such as miscellaneous crystals, cracks and pores in the manufacturing process make the domestic yield lower than 15%. During the service process, due to the harsh working environment, wear, pits and cracks appear. , the blade will be scrapped after a period of use. Repairing unqualified blades before service and damaged blades after service can save expensive superalloy materials and prolong the service life of blades. The casting cost of a single crystal blade with a complex inner cavity structure is expensive, and the cost of an engine blade is usually millions of yuan, and replacing the replacement with a single crystal blade can greatly re...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B22F7/08B22F10/25B22F10/64B33Y10/00B33Y40/20B33Y40/10
CPCB22F7/062B22F10/25B22F10/64B33Y10/00B33Y40/20B33Y40/10B22F2007/068
Inventor 不公告发明人
Owner 北京煜鼎增材制造研究院股份有限公司