Compressor Rotor Blade Airfoil Profile Optimization
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Solution Overview
Problem
Conventional airfoil designs in compressor rotor blades of gas turbines suffer from aerodynamic inefficiencies, leading to performance and efficiency losses in turbomachines.
Innovation Solution
The airfoil shape is defined by Cartesian coordinate values that form smooth continuing arcs, creating a nominal profile with a unique set of points for each Z position, which are scalable and adaptable to maintain aerodynamic and mechanical efficiency across various stages of the compressor section.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional airfoil designs are used in compressor rotor blades, then manufacturing and design are simpler, but aerodynamic efficiency is reduced
Solution Approach 1:
The patent applies parameter changes by precisely modifying the geometric parameters of the airfoil profile. Specific Cartesian coordinate values (X, Y, Z) are optimized to define the airfoil shape, including the suction side profile, pressure side profile, leading edge radius, and trailing edge geometry. These parameter optimizations reduce aerodynamic losses while maintaining manufacturability through systematic variation of dimensional parameters.
Solution Approach 2:
The patent employs curvature optimization in the airfoil design by defining smooth continuous surfaces through optimized coordinate points. The suction side and pressure side profiles utilize curved geometries with specific radius of curvature values at critical locations (leading edge, trailing edge, and along the span). This curvature optimization enhances flow attachment and reduces separation losses, improving aerodynamic efficiency.
2Productivity
If optimized airfoil profiles are designed for each Z position, then aerodynamic efficiency improves, but design and manufacturing complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the three-dimensional airfoil into a series of two-dimensional profile sections at different Z positions along the span. Each profile section is defined by optimized Cartesian coordinates (X, Y) at that specific Z location. This segmentation allows independent optimization of each cross-section while maintaining overall three-dimensional continuity, balancing performance optimization with manufacturing feasibility.
Solution Approach 2:
The patent creates a universal airfoil design framework that can be applied across different compressor stages and scales. The optimized coordinate system and profile methodology serve multiple functions: defining geometry for aerodynamic analysis, guiding manufacturing processes, and adapting to different operating conditions. This multi-functional approach reduces the need for separate designs for each application.
3Loss of energy
If smooth continuing arcs are used to connect profile sections, then aerodynamic performance improves, but manufacturing complexity increases
Solution Approach 1:
The patent applies preliminary action by pre-defining the smooth continuous surface geometry through optimized coordinate points before manufacturing. The Cartesian coordinate values are calculated and fixed in advance to ensure continuous curvature and smooth transitions between profile sections. This preliminary geometric definition eliminates the need for complex real-time manufacturing adjustments, reducing manufacturing difficulty while maintaining aerodynamic quality.
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 enhances aerodynamic efficiency and mechanical loading, allowing the gas turbine to operate efficiently, safely, and smoothly, while being robust to manufacturing tolerances and adaptable to different scales.
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 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 Table I. 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 are joined smoothly with one another to form a complete airfoil shape.