Compressor Stator Vane Airfoil Core Shape Optimization
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Solution Overview
Problem
First stage compressor stator vanes in gas turbines face challenges in achieving optimal airfoil shapes that balance aerodynamic efficiency, mechanical robustness, and manufacturability, leading to suboptimal performance and increased fuel consumption.
Innovation Solution
A specific airfoil core shape defined by Cartesian coordinate values, allowing for smooth continuation of profile sections at varying Z distances, which enhances aerodynamic and mechanical performance by optimizing airfoil geometry for compressor stator vanes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional airfoil shapes are used for compressor stator vanes, then manufacturing is easier, but aerodynamic efficiency and mechanical robustness are compromised
Solution Approach 1:
The patent applies parameter changes by precisely defining the airfoil geometry through specific Cartesian coordinate values (X, Y, Z) that optimize the shape parameters. The coordinate data in Table 1 provides exact dimensional parameters for the airfoil profile, allowing systematic optimization of aerodynamic characteristics while maintaining manufacturability through well-defined geometric parameters.
2Productivity
If optimized airfoil shapes are designed for better aerodynamic performance, then compressor efficiency improves, but manufacturing complexity increases
Solution Approach 1:
The airfoil is segmented into multiple cross-sectional profiles at different spanwise positions, each defined by specific coordinate values. This segmentation allows independent optimization of each section's aerodynamic characteristics while maintaining overall structural integrity and manufacturability through systematic coordinate definitions.
Solution Approach 2:
The patent uses detailed parameter changes by providing specific Cartesian coordinate values for each airfoil section. The precise dimensional parameters in the coordinate tables enable optimized aerodynamic performance through controlled geometric variations while keeping the manufacturing process manageable through well-defined parameters.
3Loss of energy
If airfoil shape is optimized for aerodynamic performance, then fuel consumption decreases, but design and manufacturing difficulty increases
Solution Approach 1:
The patent achieves reduced energy loss through precise parameter changes in the airfoil geometry, defined by specific coordinate values that optimize flow characteristics and reduce drag. The detailed dimensional parameters enable controlled geometric modifications that improve aerodynamic efficiency while maintaining manufacturability.
Data Source
AI summary
A turbomachine component includes a compressor stator vane having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape.