Second Stage Compressor Stator Vane Airfoil Profile Optimization
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current compressor stator vane designs in multi-stage axial compressors do not 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 multi-stage axial compressors, which define the shape and dimensions of compressor rotor blades and stator vanes to enhance compression efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a single airfoil profile design is used across multiple compressor stages, then device complexity is reduced, but compression efficiency deteriorates due to inability to match specific velocities and turning speeds of different stages
Solution Approach 1:
The patent applies local quality by providing each compressor stage with a specifically tailored airfoil profile optimized for that stage's operating conditions. Different stages receive different airfoil designs (e.g., first stage airfoil with specific coordinate values, second stage airfoil with different coordinate values) matched to their unique velocity and turning speed requirements, thereby maximizing compression efficiency at each local position in the compression system.
2Productivity
If airfoil profiles are optimized for specific stages with precise Cartesian coordinate values, then compression efficiency is improved, but manufacturing precision requirements increase
Solution Approach 1:
The patent utilizes parameter changes by providing specific sets of Cartesian coordinate values (X, Y, Z) that define the airfoil geometry. Each airfoil profile is characterized by precise numerical parameters that can be directly input into manufacturing systems, allowing for accurate reproduction of the optimized shapes while maintaining flexibility to adjust parameters for different stage requirements.
3Productivity
If conventional airfoil designs are used without stage-specific optimization, then ease of manufacture is maintained, but performance deteriorates due to suboptimal compression at different stages
Solution Approach 1:
The patent applies segmentation by dividing the compressor into distinct stages, each with its own optimized airfoil profile. This segmentation allows each stage to be independently optimized for its specific operating conditions (velocity, turning speed, pressure ratio) without compromising the manufacturing process, as each segmented airfoil design follows the same fabrication methodology with stage-specific geometric parameters.
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 compression efficiency by matching airfoil designs to specific velocities and turning speeds, resulting in better performance and operational efficiency across various stages of the compressor.
Implementation Method 1
The rotor assembly is designed to rotate with respect to the stator assembly, compressing an intake fluid as the fluid traverses the compressor
Implementation Method 2
compressing an intake fluid as the fluid traverses the compressor
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.