Compressor Blade Airfoil Profile Resonance
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Solution Overview
Problem
Compressor components with traditional airfoil designs are prone to cracking due to vibrations at specific natural frequencies, leading to efficiency losses and potential failure, which is mitigated by modifying the airfoil shape to prevent resonance.
Innovation Solution
A redesigned compressor airfoil with a specific profile, characterized by Cartesian coordinate values, is implemented to reduce vibrations by altering the tip configuration and adding a coating for corrosion resistance, thereby preventing cracking and improving airflow efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional airfoil design is used, then manufacturing is simpler, but resonance-induced cracking occurs reducing reliability
Solution Approach 1:
The patent modifies the airfoil geometry by changing specific parameters including the tip configuration, camber line shape, and cross-sectional area distribution. These parameter changes alter the natural frequency of the airfoil to avoid resonance with engine order vibrations, thereby preventing cracking while maintaining aerodynamic performance.
Solution Approach 2:
The airfoil profile incorporates asymmetric features particularly in the tip region where the cross-sectional area and camber line are optimized differently from the root section. This asymmetric design allows tailored vibration characteristics at critical locations without compromising overall structural integrity or aerodynamic efficiency.
2Reliability
If airfoil shape is modified to prevent resonance, then reliability improves, but manufacturing precision requirements increase
Solution Approach 1:
The patent applies different geometric characteristics to different sections of the airfoil. The tip region has optimized parameters for vibration resistance, while the root and mid-section maintain conventional airfoil characteristics. This localized optimization reduces the overall manufacturing precision burden compared to requiring high precision across the entire airfoil.
Solution Approach 2:
The airfoil is divided into multiple sections along the span, with each section having optimized parameters for its specific function. The tip section is segmented separately from the root section, allowing independent optimization of vibration characteristics at critical locations while maintaining standard manufacturing tolerances for other regions.
3Productivity
If tip configuration is altered to improve airflow, then compressor efficiency increases, but structural integrity may be compromised
Solution Approach 1:
The tip configuration is modified by changing geometric parameters such as the cross-sectional area distribution and camber line shape. These changes are specifically designed to improve airflow characteristics and compressor efficiency while maintaining sufficient structural strength through careful parameter selection and optimization.
Solution Approach 2:
The airfoil may incorporate composite material construction or coating treatments, particularly in the tip region, to enhance both aerodynamic performance and structural integrity. This allows the tip configuration to be optimized for airflow while the material properties provide the necessary strength and vibration resistance.
Data Source
AI summary
A compressor component having an improved airfoil profile so as to eliminate previously known vibratory issues in the blade tip is disclosed. By altering the airfoil profile throughout its span, the natural frequency of the airfoil is altered so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1.