Asymmetric Turbomachine Guide Vane Trailing Edge
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Solution Overview
Problem
Guide vane clusters in turbomachines, such as turbojet engines, experience high mechanical loads and reduced service life due to vibrations at characteristic frequencies, leading to constrained operating regions and decreased performance.
Innovation Solution
The guide vane cluster is designed with at least two vanes having different trailing edge wall thicknesses in specific radial regions, detuning their characteristic frequencies and optimizing aerodynamics through asymmetric design, which also allows for targeted structural stiffening and non-symmetric annular spaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If all vanes in the guide vane cluster have identical trailing edge wall thicknesses, then manufacturing is simplified and structural consistency is maintained, but all vanes vibrate at comparable characteristic frequencies and in phase, leading to high mechanical loads and reduced service life
Solution Approach 1:
The patent applies asymmetry by designing at least two vanes with different trailing edge wall thicknesses in the guide vane cluster. This intentional asymmetry detunes the characteristic frequencies of the vanes, preventing them from vibrating in phase and thereby reducing high mechanical loads during operation, which extends service life while maintaining manufacturing feasibility through controlled variations in trailing edge geometry
Solution Approach 2:
The patent applies local quality by varying the trailing edge wall thickness specifically in certain radial regions of selected vanes, while other portions of the vanes and other vanes in the cluster may remain identical. This localized modification allows for frequency detuning and vibration reduction without requiring complete redesign of all vanes, thus balancing manufacturing simplicity with improved reliability
2Stability of the object's composition
If all vanes in the guide vane cluster have identical trailing edge wall thicknesses, then structural uniformity is maintained, but high mechanical loads from in-phase vibrations constrict the operating region
Solution Approach 1:
The patent applies asymmetry by designing at least two vanes with different trailing edge wall thicknesses in the guide vane cluster. This intentional asymmetry detunes the characteristic frequencies of the vanes, preventing them from vibrating in phase and thereby reducing high mechanical loads during operation, which extends service life while maintaining manufacturing feasibility through controlled variations in trailing edge geometry
Solution Approach 2:
The patent applies local quality by varying the trailing edge wall thickness specifically in certain radial regions of selected vanes, while other portions of the vanes and other vanes in the cluster may remain identical. This localized modification allows for frequency detuning and vibration reduction without requiring complete redesign of all vanes, thus balancing manufacturing simplicity with improved reliability
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
This design significantly improves vibration behavior, reducing mechanical loads and extending the service life of the guide vane cluster while enhancing aerodynamic properties and structural integrity.
Implementation Method 1
the vanes thereof are thus stimulated in their characteristic form of vibration under specific operating conditions. When this occurs, high mechanical loads on the vanes or the guide vane cluster may arise, since all vanes vibrate at comparable characteristic frequencies and thus in phase
Implementation Method 2
Viewed as a disadvantage in the known guide vane clusters is the circumstance that, like all mechanical structures, they vibrate at their natural or characteristic frequencies
Data Source
AI summary
The invention relates to a guide vane cluster for a turbomachine, in particular for a turbojet engine, having at least two vanes that are joined together by way of at least one common platform for the radial delimiting of a flow channel of the turbomachine, wherein each vane has a vane element with a suction side and a pressure side that are joined together by a leading edge and a trailing edge, wherein the at least two vanes have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.