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Blade model reconstruction method supporting aerodynamic performance optimization

A technology for aerodynamic performance and model reconstruction, applied in the field of blade model reconstruction, can solve the problems of not supporting the optimization of the aerodynamic performance of the reconstructed model, not having the second function, etc., and achieving the effect of solving existing problems and strong versatility

Pending Publication Date: 2022-07-22
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

However, the existing methods only have the first function, not the second function, and cannot support the aerodynamic performance optimization of the reconstructed model

Method used

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  • Blade model reconstruction method supporting aerodynamic performance optimization
  • Blade model reconstruction method supporting aerodynamic performance optimization
  • Blade model reconstruction method supporting aerodynamic performance optimization

Examples

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specific Embodiment

[0068] Taking a compressor blade as an example, the specific implementation of the present invention will be described. damaged leaves such as figure 1 As shown, the damage location is near the intersection of the leading edge and the blade tip, and the notch has been filled with solder by a laser cladding process.

[0069] Cut the airfoil at the A-A section of the damaged position, such as figure 2 As shown, the resulting damaged blade shape is as follows image 3 shown. After analysis, there is deformation of the airfoil near the weld, such as Figure 4 As shown, the reconstructed airfoil curve needs to be smoothly connected to the unbroken curve to avoid overlapping of the blade surface.

[0070] Extract the mid-arc of the damaged blade shape, select initial repair parameters according to the blade design experience, and repair the damaged mid-arc. The curve of the missing area of ​​the original damaged blade was generated according to the complete mid-arc line and th...

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Abstract

The invention discloses a blade model reconstruction method supporting aerodynamic performance optimization, which comprises the following steps of: firstly, acquiring a three-dimensional geometric model of a repaired damaged blade, uniformly intercepting a plurality of damaged blade profiles at a damaged position, and extracting a damaged mean camber line of the blade profiles; then according to the blade profile repairing parameters, repairing the damaged mean camber line and generating a reconstruction curve of a blade profile missing area; then the damaged blade profile reconstruction curve and the undamaged curve are connected in a fairing mode, and a repaired complete blade profile is formed; after the complete blade profile is obtained, aerodynamic performance research is conducted on the complete blade profile, if the aerodynamic requirement is not met, repairing parameters are adjusted, and the steps are repeated; and finally, all the repaired complete blade profiles meeting the pneumatic requirements are fitted into a three-dimensional model, namely a blade three-dimensional reconstruction model. The method is suitable for model reconstruction of the compressor blade with the damaged front edge and rear edge, is not limited by the type, the damaged position and the damaged size of the compressor blade, and has high universality.

Description

technical field [0001] The invention belongs to the technical field of aero-engine manufacturing, and in particular relates to a blade model reconstruction method. Background technique [0002] Compressor blades are one of the most important and most used parts in aero-engines. Blades are generally made of titanium alloys and nickel-based superalloys. These materials have excellent strength, corrosion resistance and stiffness, but the characteristics of the materials and the complex manufacturing process of free-form blades cause the cost of the blades to be very high. Due to the long-term working in harsh environments, the blades will have various forms of damage such as cracks, missing, etc., and cannot continue to be used. Direct replacement of damaged blades will bring higher costs, and repairing the blades can effectively reduce the maintenance cost of the engine. [0003] At present, the commonly used blade repair method is to repair the missing part by means of lase...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06T17/00G06F30/17G06F30/20
CPCG06T17/00G06F30/17G06F30/20
Inventor 吴宝海党稼宁张莹谭淼龙张钊
Owner NORTHWESTERN POLYTECHNICAL UNIV
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