Compressor Rotor Blade Airfoil Profile Optimization
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Solution Overview
Problem
Existing airfoil designs for compressor rotor blades in gas turbine systems suffer from aerodynamic inefficiencies, leading to energy losses and reduced performance.
Innovation Solution
The airfoil shape is defined by Cartesian coordinate values that form a nominal profile, with smooth continuing arcs connecting the profile sections at each Z value, resulting in improved aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional airfoil designs are used, then the structure is simple and easy to manufacture, but aerodynamic efficiency is reduced due to energy losses
Solution Approach 1:
The patent applies parameter changes by precisely modifying the geometric parameters of the airfoil profile using specific Cartesian coordinate values. The detailed coordinate data in Tables I and II define optimized positions for profile sections along the span, creating a tailored geometry that reduces aerodynamic losses while maintaining manufacturability through systematic parameter specification.
Solution Approach 2:
The invention implements local quality by varying the airfoil profile characteristics at different span locations (Z-values). Each station along the blade span has uniquely optimized X and Y coordinates that create locally adapted profile shapes, allowing the airfoil to have different geometric properties at different locations to minimize energy losses in specific flow regions.
2Productivity
If the airfoil profile is optimized for aerodynamic efficiency, then energy losses are reduced, but the manufacturing precision requirements increase
Solution Approach 1:
The patent applies segmentation by dividing the airfoil profile into multiple discrete span stations with specific Z-coordinate values. Each station has defined X and Y coordinates that can be independently specified and manufactured. This segmentation allows the complex three-dimensional profile to be broken down into manageable two-dimensional sections that can be manufactured and assembled with controlled precision at each station.
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 new airfoil shape enhances aerodynamic efficiency, reducing energy losses and improving the overall performance of the compressor rotor blades and turbomachines.
Implementation Method 1
the airfoils are configured to aerodynamically interact with the fluid flows and to transfer energy to or from these fluid flows
Implementation Method 2
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. Advantageously, this airfoil shape tends to provide for improved aerodynamic efficiency of the airfoil
Data Source
AI summary
A rotor blade 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 and TABLE II. 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.