Compressor Turbomachine Blade Leading-Edge Geometry for FOD Resistance
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Solution Overview
Problem
Existing compressor blades in turbomachines face challenges in balancing structural integrity and aerodynamic efficiency, particularly due to conflicting requirements for robustness against foreign object damage and optimal geometry for airflow efficiency.
Innovation Solution
The design of compressor blades incorporates a leading-edge ratio parameter greater than 5.5, defined by the product of relative leading-edge thickness and leading-edge wedge angle, to enhance mechanical strength and aerodynamic performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the blade leading edge is made slender to increase aerodynamic efficiency, then the efficiency and surge line distance are improved, but the structural robustness against foreign object damage deteriorates
Solution Approach 1:
The patent introduces a new geometric parameter combination (leading edge ratio parameter = relative leading edge thickness × leading edge wedge angle) that must exceed 5.5 to simultaneously achieve both aerodynamic efficiency and FOD resistance. This parameter transformation allows optimization of the blade geometry by changing the relationship between thickness and wedge angle rather than using either parameter alone.
Solution Approach 2:
The patent applies different geometric characteristics to different regions of the blade leading edge. By controlling the local geometry through the wedge angle and thickness distribution, the blade achieves optimal performance in the critical leading edge region while maintaining overall aerodynamic efficiency. The leading edge ratio parameter specifically governs the local quality of the leading edge geometry.
2Reliability
If the relative leading edge thickness is increased to improve structural strength, then the robustness against foreign object damage is improved, but the aerodynamic efficiency deteriorates
Solution Approach 1:
Instead of maximizing relative leading edge thickness alone, the patent optimizes the product of relative leading edge thickness and leading edge wedge angle. This allows achieving sufficient structural strength through the thickness component while using a smaller wedge angle to maintain aerodynamic efficiency, rather than increasing both parameters independently.
Solution Approach 2:
The solution combines two geometric parameters (relative leading edge thickness and leading edge wedge angle) into a composite design approach. The leading edge ratio parameter integrates both parameters to achieve a balanced geometry that satisfies both structural and aerodynamic requirements simultaneously.
3Reliability
If the leading edge wedge angle is increased to improve structural integrity, then the robustness against foreign object damage is improved, but the aerodynamic performance deteriorates
Solution Approach 1:
The patent optimizes the leading edge wedge angle in conjunction with the relative leading edge thickness. By controlling their product to exceed 5.5, the design achieves sufficient structural integrity through the combined effect rather than relying on a large wedge angle alone, thereby maintaining aerodynamic performance.
Data Source
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AI summary
The invention relates to a blade (10) for a compressor of a turbomachine, which extends from a blade root (31) between a leading edge (11) and a trailing edge (12) to a blade tip (32), wherein the leading edge (11) has a leading edge thickness (dLE) and the blade (11) has a maximum profile thickness (dmax), the ratio of which to each other represents a relative leading edge thickness (vkdrel), and the blade (11) has a leading edge wedge angle (αw).