Cast isometric crystal high-temperature alloy turbine rotor blade tip repairing method and tool

A high-temperature alloy and turbine rotor technology, which is applied in the direction of additive processing, energy efficiency improvement, process efficiency improvement, etc., can solve problems such as interference in the process of parts and equipment, difficulty in accurately positioning the electron beam, and the combination of printing materials and base materials. , to achieve the effect of improving repair efficiency and quality, small heat input, and small machining allowance

Active Publication Date: 2020-12-08
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, laser selective melting and electron beam selective melting are processes used to directly manufacture parts. There has been no method for repairing parts before. To use them for blade tip repair needs to overcome many difficulties: the clamping and positioning of parts is difficult, and the parts are not suitable for equipment. There is interference in the process, there is no 3D digital model in the repaired part, it is difficult to accurately position the laser and electron beams in the repaired area when the part is printed, and the printing material is combined with the base material, etc.

Method used

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  • Cast isometric crystal high-temperature alloy turbine rotor blade tip repairing method and tool
  • Cast isometric crystal high-temperature alloy turbine rotor blade tip repairing method and tool
  • Cast isometric crystal high-temperature alloy turbine rotor blade tip repairing method and tool

Examples

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Effect test

specific example 1

[0048] EOS M290 laser selective melting (SLM) equipment was used to repair the wear damage of the K4002 cast equiaxed crystal superalloy turbine blade tip of a certain type of engine. The specific steps are as follows:

[0049] S1. Tool design and blade clamping: Design a tool to assist blade positioning, clamping and laser selective melting (SLM) repair. For the designed tooling shape and clamping method, see figure 1 and figure 2 .

[0050] see Figure 1 to Figure 4 , The tooling designed in the present invention includes a base block 1 , a substrate base 2 , a bolt 3 and a locking block 4 .

[0051] The size of the base block 1 is 150mm (length) × 50mm (width) × 120mm (height), welded to the surface of the substrate base, and the angle between the two base blocks is 90° and placed at a right angle;

[0052] The size of the substrate base 2 is 252mm (length) × 252mm (width) × 45mm (thickness). There are M5 threaded holes on the substrate base, which can cooperate with b...

specific example 2

[0068] Arcam A2X Electron Beam Selective Melting (EBM) equipment was used to repair the tip wear damage of K4002 cast equiaxed superalloy turbine blades of a certain type of engine. The specific steps are as follows:

[0069] S1. Tool design and blade clamping: Design a tool to assist blade positioning, clamping and electron beam melting (EBM) repair. For the designed tooling shape and clamping method, see figure 1 and figure 2 .

[0070] see Figure 1 to Figure 4 , The tooling designed in the present invention includes a base block 1 , a substrate base 2 , a bolt 3 and a locking block 4 .

[0071] The size of the base block 1 is 150mm (length) × 50mm (width) × 120mm (height), welded to the surface of the substrate base, and the angle between the two base blocks is 90° and placed at a right angle;

[0072] The size of the substrate base 2 is 252mm (length) × 252mm (width) × 45mm (thickness), and there are M5 threaded holes in the substrate base, which can cooperate with t...

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Abstract

The invention belongs to the technical field of aero-engine maintenance, and relates to a cast isometric crystal high-temperature alloy turbine rotor blade tip repairing method and tool. According tothe method, repairing is completed through a laser selective melting or electron beam selective melting process, a blade can be placed in a forming area of laser selective melting or electron beam selective melting equipment and formed at a blade tip through the tool, data are obtained through three-dimensional scanning for reverse modeling, a model needing to be repaired and formed and related position information are obtained, the corresponding tool and blade clamping are designed, the structure and form of the tool are not limited, and the tool can be used for completing blade clamping, auxiliary positioning and position calibration; printing repairing forming is conducted after positioning calibration, and finally aftertreatment and detection are completed; and the positioning precision of blade repairing is well controlled, and the beneficial effects that the cast isometric crystal high-temperature alloy turbine rotor blade tip repairing method and tool is small in heat input, fine in grains, excellent in mechanical property, small in deformation, excellent in surface roughness and high in size precision, near-net forming does not need machining, and forming is rapid and efficient are achieved.

Description

technical field [0001] The invention belongs to the technical field of aero-engine maintenance, and relates to the repair of hot-end parts of the engine, in particular to a method and tooling for repairing the blade tip of a cast equiaxed superalloy turbine rotor blade. Background technique [0002] The working environment of cast equiaxed superalloy turbine rotor blades is high temperature and high pressure, and the blade tip is easily damaged, which requires a lot of repair work on the blade tip. The traditional repair method is to use welding techniques such as laser welding to surfacing on the top of the blade, and then perform machining and grinding to remove excess material to complete the repair. This method has many problems such as large welding deformation, large heat input affecting the structure and performance of the blade, poor surface roughness, poor dimensional accuracy, difficult machining, low efficiency, and high cost. Therefore, there is an urgent need f...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B22F3/105B22F7/06B33Y10/00B33Y30/00
CPCB22F7/062B33Y10/00B33Y30/00B22F2007/068Y02P10/25
Inventor 张学军马宇超赵海生孙兵兵张强秦仁耀
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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