Compressor Airfoil Shape for Stage 16 Stress Reduction
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Solution Overview
Problem
Current stator compressor vane airfoil designs face challenges in achieving optimal aerodynamic efficiency and reducing thermal and mechanical stresses across various stages of a gas turbine, particularly in Stage 16, where existing profiles fail to balance efficiency and stress requirements effectively.
Innovation Solution
A unique airfoil shape defined by specific Cartesian coordinates (X, Y, Z) is introduced, which improves aerodynamic efficiency and reduces thermal and mechanical stresses by providing a robust profile that maintains mechanical and aerodynamic functions despite manufacturing tolerances and temperature changes, allowing for scaling while retaining the airfoil section shape.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional airfoil profiles are used in Stage 16, then manufacturing and design are simpler, but aerodynamic efficiency is insufficient and thermal/mechanical stresses are not adequately reduced
Solution Approach 1:
The patent applies parameter changes by precisely adjusting the geometric parameters of the airfoil profile through defined Cartesian coordinates (X, Y, Z). The specific coordinate values in Table 1 represent optimized parameters that simultaneously improve aerodynamic efficiency and reduce thermal and mechanical stresses in Stage 16, resolving the contradiction between performance improvement and design complexity.
2Productivity
If the airfoil profile is optimized for aerodynamic efficiency, then compressor performance improves, but thermal and mechanical stresses increase
Solution Approach 1:
The patent applies local quality by creating non-uniform distribution of material properties and geometric characteristics along the airfoil structure. The varying cross-sectional shapes defined by different Z-coordinate positions allow the airfoil to have optimized local properties - thicker sections where structural strength is needed and thinner sections where aerodynamic efficiency is prioritized, thus simultaneously improving compressor performance while managing thermal and mechanical stresses.
3Reliability
If the airfoil profile is designed for high efficiency, then aerodynamic performance improves, but manufacturing precision requirements increase
Solution Approach 1:
The patent applies segmentation by dividing the continuous airfoil profile into discrete measurable sections defined by specific Z-coordinate positions. Each cross-section at a given Z position is defined by specific X and Y coordinates, creating a segmented framework that simplifies manufacturing control. This segmentation allows for systematic quality inspection and tolerance management while maintaining overall aerodynamic efficiency.
Data Source
AI summary
An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. 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 shape.