Guide Vane Fibrous Preform With Unidirectional Vibration Stiffeners
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Turbomachine blades made of composite material face challenges in reducing mass while maintaining optimized mechanical resistance, particularly against vibratory stresses that can induce undesirable vibration modes and geometric modifications, potentially damaging the part and impacting engine performance.
Innovation Solution
Incorporation of fibrous vibration damping stiffeners, comprising unidirectional layers of threads, within the fiber preform to oppose and dampen problematic vibration modes, optimizing stiffness and limiting material embrittlement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If composite material is used to reduce mass, then weight is reduced, but mechanical resistance against vibratory stresses deteriorates
Solution Approach 1:
The invention uses a composite structure combining woven fiber portions for mass reduction with unidirectional fiber stiffeners for vibration damping. This multi-material approach allows simultaneous weight reduction and mechanical resistance enhancement by strategically placing different fiber architectures in specific locations within the blade structure.
Solution Approach 2:
The invention applies different fiber architectures (woven vs. unidirectional) in different locations within the blade. The unidirectional stiffeners are specifically placed in regions experiencing high vibratory stresses, while woven portions are used in other areas for mass reduction. This localized differentiation optimizes both weight and mechanical resistance where needed.
2Weight of moving object
If conventional woven fiber reinforcement is used, then mass is reduced, but vibration damping capability deteriorates
Solution Approach 1:
The invention combines woven fiber portions (for mass reduction) with unidirectional fiber stiffeners (for vibration damping) in a composite structure. This allows the blade to simultaneously achieve weight reduction while gaining vibration damping capability through the synergistic combination of different material architectures.
Solution Approach 2:
The invention places unidirectional stiffeners specifically in regions where vibration damping is most needed, while using woven portions elsewhere for mass reduction. This localized placement of different fiber types optimizes vibration damping performance without compromising overall mass reduction goals.
3Strength
If fibrous stiffeners are added to dampen vibrations, then mechanical resistance is improved, but device complexity increases
Solution Approach 1:
The invention divides the fiber reinforcement into distinct segments: woven fiber portions for mass reduction and separate unidirectional stiffener elements for vibration damping. This segmentation allows each component to perform its specific function independently while being integrated into a unified blade structure, managing complexity through functional decomposition.
Solution Approach 2:
The invention merges the woven fiber portions and unidirectional stiffeners into a single integrated preform structure that is manufactured and cured as one piece. This combining approach, while adding functional complexity, simplifies the overall manufacturing process by eliminating the need for separate assembly steps, thus managing device complexity through integration.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The fibrous stiffeners effectively dampen vibration modes, enhancing mechanical resistance and reducing the risk of material damage, thereby improving the performance and service life of turbomachine blades.
Implementation Method 1
each fiber portion has at least one fiber stiffener for damping vibrations comprising one or more unidirectional layers of threads
Data Source
Figure 1~2
Figure 3~3A
Figure 4~5
AI summary
The invention relates to a fibrous preform (10) for a guide vane of a gas turbine engine, wherein the preform (10) comprises two fibrous portions (14) forming an airfoil of the vane and defining therebetween an interior volume (16), and wherein each fibrous portion has at least one vibration-damping fibrous stiffener (19a; 19b) that comprises one or more unidirectional yarn layers (191a; 191b) and is present in the inner volume.