Compressor Stator Vane Airfoil Cartesian Coordinate Optimization
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Solution Overview
Problem
Conventional airfoil designs for compressor stator vanes in gas turbines suffer from aerodynamic inefficiencies, leading to performance losses and reduced system efficiency in power generation.
Innovation Solution
The airfoil shape is defined by specific Cartesian coordinate values in Tables I-VIII, which when scaled, form smooth continuing arcs and surfaces, creating a nominal profile that enhances aerodynamic efficiency by optimizing the suction-side and pressure-side surfaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional airfoil designs are used for compressor stator vanes, then manufacturing and design simplicity is maintained, but aerodynamic efficiency is reduced leading to performance losses
Solution Approach 1:
The patent applies parameter changes by defining the airfoil geometry through specific Cartesian coordinate values (X, Y, Z) that optimize the suction-side and pressure-side surfaces. The coordinate data in Tables I-VIII provides precise dimensional parameters for the airfoil profile, allowing optimization of aerodynamic performance through controlled variation of geometric parameters while maintaining manufacturability through systematic definition.
Solution Approach 2:
The patent utilizes curvature principles by defining smooth continuing arcs that connect the X and Y coordinate values at each Z position. This creates a continuously curved airfoil surface without sharp edges or discontinuities, which reduces flow separation and turbulence. The smooth curvature is maintained throughout the airfoil profile from leading edge to trailing edge, optimizing aerodynamic efficiency.
2Productivity
If optimized airfoil profiles with smooth continuing arcs are implemented, then aerodynamic efficiency is improved, but manufacturing precision requirements increase
Solution Approach 1:
The patent applies segmentation by dividing the airfoil geometry into discrete coordinate points along the Z-axis, with each position defined by specific X and Y values. This segmentation allows the complex curved surface to be constructed from a series of manageable coordinate points that can be precisely manufactured and measured. The coordinate data is presented in tabular form with specific Z-position intervals, making manufacturing and quality control more feasible.
Solution Approach 2:
The patent provides specific numerical parameter values for each coordinate point in Tables I-VIII, allowing manufacturers to achieve the desired precision through controlled parameter specification. The non-dimensionalized coordinate system with scaling factors enables flexible adaptation to different airfoil sizes while maintaining the same geometric relationships, reducing the complexity of manufacturing at different scales.
3Adaptability or versatility
If non-dimensionalized Cartesian coordinate values are used to define the airfoil, then adaptability to different scales is improved, but design complexity increases
Solution Approach 1:
The patent applies universality by using a non-dimensionalized coordinate system that can define airfoil geometry at any scale. The same set of non-dimensionalized X, Y, Z values in Tables I-VIII can be used for small or large airfoils by applying an appropriate scaling factor. This universal coordinate system eliminates the need to redesign the airfoil geometry for different applications, allowing the same optimized profile to be scaled to various sizes while maintaining aerodynamic performance.
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 improves aerodynamic efficiency of the airfoil, leading to enhanced performance and reduced losses in the compressor section of gas turbines, resulting in improved power generation and system efficiency.
Implementation Method 1
The 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 having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, or Table VIII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% 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, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.