Compressor Stator Vane Airfoil Shape Optimization
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Solution Overview
Problem
Existing airfoils in compressor stator vanes of gas turbine systems suffer from aerodynamic inefficiencies, leading to energy losses and reduced performance.
Innovation Solution
The airfoil shape is defined by specific Cartesian coordinate values, which are non-dimensional and scalable, to optimize the aerodynamic profile of the stator vanes, particularly in the fifth, sixth, and seventh compressor stages.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional airfoil shapes are used in compressor stator vanes, then manufacturing and design are simpler, but aerodynamic losses increase and efficiency decreases
Solution Approach 1:
The patent applies parameter changes by precisely modifying the geometric parameters of the airfoil shape through specific Cartesian coordinate values. The optimized coordinates define the pressure side and suction side profiles, transforming the airfoil geometry to reduce flow separation and minimize aerodynamic losses while maintaining manufacturability through systematic parameter optimization.
Solution Approach 2:
The patent utilizes curvature optimization by defining smooth continuous arcs connecting the Cartesian coordinate points to form the airfoil profile. The optimized curvature distribution along the pressure and suction sides reduces flow separation and minimizes turbulence, directly addressing aerodynamic losses through geometric shaping principles.
2Productivity
If airfoil shape is optimized for aerodynamic efficiency, then energy transfer improves, but design and manufacturing precision requirements increase
Solution Approach 1:
The patent applies segmentation by dividing the airfoil profile into discrete Cartesian coordinate points that define the geometry. This segmentation allows precise control of the airfoil shape through specific coordinate values while enabling manufacturing through point-by-point fabrication or molding, balancing aerodynamic optimization with manufacturing feasibility.
Solution Approach 2:
The patent uses parameter changes by providing specific numerical Cartesian coordinate values that define the optimized airfoil geometry. These parameters can be precisely controlled during manufacturing, and the non-dimensionalized format allows scaling to different sizes while maintaining the optimal shape characteristics for energy transfer efficiency.
3Adaptability or versatility
If non-dimensional scalable coordinates are used to define airfoil shape, then adaptability to different compressor stages improves, but design complexity increases
Solution Approach 1:
The patent applies universality by providing non-dimensionalized Cartesian coordinate values that can be scaled to different sizes and applied to various compressor stages (fifth, sixth, and seventh stages). This universal coordinate system allows the same optimized airfoil shape to be adapted across multiple applications by simply applying a scaling factor, enhancing versatility without requiring separate designs for each stage.
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
The optimized airfoil shape reduces aerodynamic losses, enhancing the efficiency and performance of the gas turbine system by improving energy transfer and fluid flow management.
Implementation Method 1
These airfoils are configured to aerodynamically interact with the fluid flows and to transfer energy to or from these fluid flows
Data Source
AI summary
A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in one of TABLE I, TABLE II, or TABLE III. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at a base of the airfoil. The Cartesian coordinate values of X, Y, and Z are non-dimensional values that are convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.