Scalable Airfoil Profile Design for Compressor Efficiency
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Solution Overview
Problem
Turbomachinery airfoils in compressors face challenges in achieving optimal efficiency, reducing vibratory response, and meeting mechanical and thermal operating requirements while maintaining reliability and cost targets.
Innovation Solution
The airfoil profile is defined using scalable Cartesian coordinate values in Tables 1-11, which are non-dimensional and convertible to dimensional distances, allowing for the creation of complete airfoil shapes that can be scaled up or down, ensuring efficient and reliable operation by defining unique loci of points for aerodynamic and mechanical loadings.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If conventional airfoil profiles are used, then manufacturing and design are simpler, but compressor efficiency and aerodynamic performance are suboptimal
Solution Approach 1:
The patent applies parameter changes by systematically varying airfoil geometric parameters (thickness distribution, camber, leading edge radius, trailing edge geometry) to optimize aerodynamic performance. Multiple airfoil profiles with different parameter sets are provided, allowing selection based on specific compressor stage requirements to achieve optimal efficiency while managing complexity.
Solution Approach 2:
The patent implements local quality by optimizing different sections of the airfoil profile with distinct characteristics - the leading edge is designed with specific radius curvature for smooth flow attachment, the mid-section has optimized thickness distribution for structural strength and flow control, and the trailing edge has specific geometry for proper flow separation control. Each local region is tailored to its functional requirements.
2Productivity
If airfoil loading is increased to meet design goals, then compressor size can be reduced, but vibratory response and mechanical stress increase
Solution Approach 1:
The patent applies dynamics by providing multiple airfoil profiles optimized for different operating conditions and load levels. The selection of appropriate airfoil profile from the set allows the compressor to adapt to varying operational requirements, maintaining optimal performance across different loading scenarios while managing vibratory responses through appropriate profile selection.
Solution Approach 2:
The patent utilizes curvature optimization in the airfoil profiles, with carefully designed leading edge radius, camber curvature distribution, and trailing edge curvature. These curved geometries are optimized to control flow attachment and separation characteristics, reducing adverse pressure gradients and minimizing vibratory responses while maintaining effective loading.
3Use of energy by moving object
If airfoil profile is optimized for aerodynamic performance, then efficiency improves, but manufacturing precision requirements increase
Solution Approach 1:
The patent applies segmentation by providing airfoil profiles with standardized geometric parameters and dimensional tolerances that can be manufactured using conventional processes. The profiles are defined with practical tolerance ranges that balance aerodynamic performance with manufacturability, allowing分段 manufacturing and assembly where applicable.
Solution Approach 2:
The patent modifies parameters by providing airfoil profiles with optimized geometric parameters that achieve good aerodynamic performance within practical manufacturing tolerances. The parameter sets are selected to be robust to typical manufacturing variations, ensuring consistent performance without requiring excessive precision.
Data Source
AI summary
An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.