Third Stage Compressor Stator Vane Airfoil Profile
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Solution Overview
Problem
Current compressor stator vane designs in multi-stage axial compressors do not fully optimize airfoil profiles for specific stages, leading to suboptimal compression efficiency and performance.
Innovation Solution
The development of airfoil profiles with specific Cartesian coordinate values for suction and pressure sides, optimized for specific stages of the compressor, which are convertible to dimensional distances, enhancing the compression efficiency by matching velocities and turning speeds.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a generic airfoil profile is used for compressor stator vanes across multiple stages, then the device complexity is reduced and manufacturing is simplified, but the compression efficiency and performance are suboptimal
Solution Approach 1:
The patent applies local quality by providing different airfoil profile coordinate values for different compressor stages (first stage through fifth stage). Each stage has specifically optimized X, Y, and Z coordinate values that match the local flow conditions and velocity requirements of that particular stage, thereby maximizing compression efficiency at each location rather than using a uniform profile throughout.
2Productivity
If airfoil profiles are optimized for specific stages with precise Cartesian coordinate values, then compression efficiency is enhanced, but the manufacturing precision requirements increase
Solution Approach 1:
The patent utilizes parameter changes by providing specific sets of X, Y, and Z coordinate values for each compressor stage. These parameters are carefully selected and optimized to match the velocity and turning requirements of each stage. The non-dimensionalized coordinate system allows for systematic variation of geometric parameters while maintaining manufacturing feasibility.
3Adaptability or versatility
If non-dimensional Cartesian coordinate values are used for airfoil profiles, then adaptability across different compressor configurations is improved, but the conversion to dimensional distances adds computational steps
Solution Approach 1:
The patent applies universality by using a non-dimensionalized coordinate system for all airfoil profiles across different compressor stages. This universal approach allows the same set of coordinate values to be scaled and applied to various compressor configurations and sizes. The non-dimensional parameters serve multiple functions: they enable geometric similarity, facilitate computational fluid dynamics analysis, and simplify the adaptation of airfoil profiles to different operating conditions.
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 profiles improve the efficiency of the multi-stage axial compressor by enhancing compression performance and energy transfer, leading to better operational outcomes.
Implementation Method 1
The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side
Data Source
AI summary
A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.