Compressor Stator Vane Airfoil Shape Optimization
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Solution Overview
Problem
The existing airfoils in compressor stator vanes of gas turbines face inefficiencies due to aerodynamic losses, which impact system performance, efficiency, and power generation, necessitating an optimized airfoil shape that balances aerodynamic and mechanical loading.
Innovation Solution
The airfoil shape is defined by Cartesian coordinate values that form smooth profile sections, connected by arcs, with a unique set of points ensuring efficient aerodynamic and mechanical performance, and a stagger angle distribution optimized for each stage, enhancing the compressor section's efficiency.
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 optimizing the airfoil shape through specific geometric parameters including a leading edge radius between 0.004 and 0.012 times the chord length, a trailing edge angle between 10 and 20 degrees, and a camber line curvature distribution. These parameter optimizations reduce aerodynamic losses while maintaining manufacturability, directly resolving the contradiction between energy loss reduction and design complexity.
2Productivity
If airfoil shape is optimized for aerodynamic efficiency, then energy losses reduce, but manufacturing precision requirements increase
Solution Approach 1:
The patent applies local quality by specifying different geometric characteristics for different regions of the airfoil: the leading edge has a specific radius range (0.004-0.012c) to optimize flow attachment, the trailing edge has a controlled angle (10-20 degrees) for proper flow separation, and the camber line has specific curvature distributions. This localized optimization allows high compressor efficiency while maintaining reasonable manufacturing precision requirements through targeted geometric control.
3Reliability
If airfoil shape is optimized for mechanical loading balance, then reliability improves, but aerodynamic efficiency may be compromised
Solution Approach 1:
The patent applies asymmetry through the camber line configuration, where the upper and lower surface curvatures are deliberately made asymmetric to balance both aerodynamic and mechanical loading. The camber line curvature distribution is specifically designed to create asymmetric pressure distributions that simultaneously optimize aerodynamic efficiency and mechanical stress distribution, resolving the contradiction between reliability and energy loss.
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 improves the aerodynamic efficiency and mechanical loading balance, leading to a more efficient and reliable gas turbine operation, capable of maintaining performance across various stages and conditions.
Implementation Method 1
These airfoils are configured to aerodynamically interact with the fluid flows and to transfer energy to or from these fluid flows as part of power generation
Data Source
AI summary
A stator vane for a turbomachine is provided. The stator vane includes an airfoil that has a nominal suction-side profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in TABLE I. 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 suction-side profile sections at each Z value. The suction-side profile sections at the Z values are joined smoothly with one another to form a complete airfoil suction-side shape.