3D Woven Composite Turbine Blade Preform

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Solution Overview

Problem

The existing methods for manufacturing composite turbine engine blades, particularly fan blades, are labor-intensive and costly due to the need for manual fold stacking and subsequent precise machining, which can compromise mechanical strength and introduce fragility at assembly zones, leading to issues like delamination and reduced thermomechanical resistance.

Innovation Solution

A method involving a three-dimensional woven preform with tracer yarns that are not cut during injection molding, allowing for pre-deformation and compaction to achieve a shape close to the final part, thereby preserving fiber integrity and enabling the installation of protective elements during injection molding, reducing the need for extensive machining and enhancing mechanical properties.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If manual fold stacking of unidirectional prepreg plies is used to manufacture composite blades, then the blade can be formed with proper fiber orientation, but the process becomes labor-intensive, time-consuming, and expensive

Engineering Contradiction:
Improvemanufacturing process simplicityVSAvoidproduction time and cost
Core Design Contradiction:
Ease of manufactureVSProductivity

Solution Approach 1:

The invention segments the manufacturing process by using pre-woven three-dimensional preforms that come in ready-to-use configurations, eliminating the need for manual stacking of individual plies. The preforms are designed with integrated fiber orientations that match the final blade geometry, allowing direct placement into molds without complex assembly operations.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

The fiber reinforcement structure is pre-formed into three-dimensional woven preforms before the molding process. These preforms are prepared in advance with the correct geometry, fiber distribution, and orientation patterns, so that when placed in the mold, they require minimal additional manipulation and no manual stacking operations.

Inventive Principle:
Principle #10Preliminary action

2Manufacturing precision

If subsequent precise machining is performed on the polymerized preform to achieve final dimensions, then the blade contours and bearing surfaces meet construction requirements, but the mechanical strength is reduced due to cutting of fiber threads

Engineering Contradiction:
Improveblade contour and surface precisionVSAvoidfiber integrity and mechanical strength
Core Design Contradiction:
Manufacturing precisionVSStrength

Solution Approach 1:

The preforms are pre-shaped and pre-compacted to very close tolerances before polymerization, anticipating the final blade geometry. The three-dimensional weaving pattern and pre-forming process create surfaces that require minimal post-processing, preserving fiber continuity while achieving the required dimensional accuracy for contours and bearing surfaces.

Inventive Principle:
Principle #10Preliminary action

Solution Approach 2:

The invention changes the physical state and properties of the preform through controlled compaction and pre-forming operations. By adjusting density, fiber orientation, and surface finish parameters during the pre-forming stage, the material achieves near-final dimensions and surface quality, reducing the need for aggressive machining that would cut fibers.

Inventive Principle:
Principle #35Parameter changes

3Reliability

If protective elements are installed after injection molding, then the blade gains thermomechanical resistance, but the implementation time and economic cost increase significantly

Engineering Contradiction:
Improvethermomechanical resistanceVSAvoidimplementation time
Core Design Contradiction:
ReliabilityVSLoss of time

Solution Approach 1:

The invention merges the protective element installation with the injection molding process itself. Protective coatings, surface treatments, or reinforcement layers are applied to the preform before or during polymerization, so that the blade emerges from molding already equipped with its protective elements. This eliminates separate post-processing steps and reduces total implementation time.

Inventive Principle:
Principle #5Merging (Combining)

Solution Approach 2:

Protective elements are pre-installed on the preform before the injection molding operation. Surface coatings, protective films, or reinforcement layers are applied in advance, and the preform is then molded with these protective elements already in place, integrating protection into the primary manufacturing step rather than adding it later.

Inventive Principle:
Principle #10Preliminary action

4Adaptability or versatility

If assembly zones are created by sewing or inserting separate parts, then the blade can be constructed from multiple components, but delamination occurs at these zones creating privileged sites of fragility

Engineering Contradiction:
Improveblade design flexibilityVSAvoidresistance to delamination and impact
Core Design Contradiction:
Adaptability or versatilityVSReliability

Solution Approach 1:

The invention uses three-dimensional woven preforms that are internally segmented into functional zones through the weaving pattern itself, rather than assembling separate physical components. Different regions of the preform can have different fiber orientations, densities, or material properties built into the weave structure, providing design flexibility without creating weak interfaces between joined parts.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

The invention employs three-dimensional woven composite preforms where multiple fiber directions and layers are integrated into a single continuous structure. This creates a monolithic composite material with through-thickness reinforcement and interlaced fiber paths that prevent delamination, eliminating the need to assemble separate components that would create vulnerable joint zones.

Inventive Principle:
Principle #40Composite materials

Data Source

PatentEP1777063B1Manufacturing process of a composite turbine blade and the blade obtained thereby
Publication Date: 2012.07.04 SN DETUDE & DE CONSTR DE MOTEURS DAVIATION (S N E C M A)
  • EP1777063B1 patent drawingFigure 1~3
  • EP1777063B1 patent drawingFigure 4~6

AI summary

The invention relates to a method for manufacturing a composite turbomachine blade, wherein: a) a preform is produced by weaving in three dimensions yarns comprising tracer yarns (22) arranged at least on the surface of the preform; b) said preform is cut, leaving intact a series of tracer yarns (22) located along a reference face of the preform; c) said cut preform (10a) is pre-deformed; d) said pre-deformed preform is compacted and stiffened; e) an injection mold is provided into which said stiffened preform is placed; f) said injection mold is heated; g) a binder comprising a thermosetting resin is injected into said injection mold; and h) a composite molded part having substantially the shape and dimensions of said blade is removed from the mold. Application to a blower blade.