Composite Airfoil Ply Stacking with Hybrid Manufacturing

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Solution Overview

Problem

Existing methods for manufacturing composite airfoils face challenges in balancing efficiency and precision, particularly in the integration of automated and manual processes, which can compromise the strength and complexity of the assembly.

Innovation Solution

A hybrid manufacturing method is employed, combining automated processes for larger sections and manual processes for smaller, harder-to-reach areas, utilizing different sets of plies with varying fiber lengths and materials to construct a composite airfoil, ensuring both efficiency and precision.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Productivity

If automated processes are used for stacking plies, then productivity is improved, but manufacturing precision deteriorates

Engineering Contradiction:
Improvemanufacturing efficiencyVSAvoidply placement precision
Core Design Contradiction:
ProductivityVSManufacturing precision

Solution Approach 1:

The airfoil is divided into multiple sections (first section, second section, third section) with different stacking requirements. Automated processes are applied to the first section where precision is less critical, while manual processes are used for the second and third sections where higher precision is needed for complex geometries and hard-to-reach areas.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

Different manufacturing approaches are applied to different regions of the airfoil based on local requirements. The first section uses automated stacking for efficiency, while the second and third sections use manual stacking to achieve the required precision for complex shapes and tight tolerances in hard-to-reach areas.

Inventive Principle:
Principle #3Local quality

2Manufacturing precision

If manual processes are used for stacking plies, then manufacturing precision is improved, but productivity deteriorates

Engineering Contradiction:
Improveply placement precisionVSAvoidmanufacturing efficiency
Core Design Contradiction:
Manufacturing precisionVSProductivity

Solution Approach 1:

The airfoil manufacturing process is segmented into multiple sections, with manual processes reserved for specific sections (second and third sections) where precision is critical, while automated processes handle the first section to maintain overall productivity.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

Manual stacking is applied locally to sections requiring high precision (second and third sections with complex geometries), while automated stacking is used in sections where precision requirements are lower, optimizing the balance between precision and productivity for each local region.

Inventive Principle:
Principle #3Local quality

3Ease of manufacture

If hybrid manufacturing process is used, then ease of manufacture is improved, but device complexity increases

Engineering Contradiction:
Improvemanufacturing flexibilityVSAvoidprocess integration complexity
Core Design Contradiction:
Ease of manufactureVSDevice complexity

Solution Approach 1:

The manufacturing process is segmented into distinct sections with different methods (automated for first section, manual for second and third sections), allowing each segment to be optimized independently while maintaining overall manufacturing flexibility and ease of implementation.

Inventive Principle:
Principle #1Segmentation

Data Source

PatentEP4620657A1Method and system of forming a composite airfoil having a set of plies
Publication Date: 2025.09.24 GENERAL ELECTRIC CO
  • EP4620657A1 patent drawingFigure 1
  • EP4620657A1 patent drawingFigure 2
  • EP4620657A1 patent drawingFigure 3

AI summary

A method (380) of forming an assembly (100). The assembly (100) having a stack of plies (177) and an airfoil portion (110). The airfoil portion has an outer wall (172) extending between a root (118) and a tip (120) in a spanwise direction (Sd), and between a leading edge (114) and a trailing edge (116). The assembly (100) has a first set of plies (140) and a second set of plies (142). The first set of plies (140) form at least a portion of the airfoil portion (110).