Compressor Inlet Guide Vane Airfoil Profile Optimization
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Solution Overview
Problem
Current compressor designs for gas turbine systems face inefficiencies in compressing gases due to suboptimal airfoil profiles, leading to reduced performance and energy consumption across multiple stages.
Innovation Solution
The development of specific airfoil profiles for compressor rotor blades and stator vanes, defined by Cartesian coordinate values, which are optimized for specific velocities and turning speeds, enhancing compression efficiency across multiple stages of the compressor.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If conventional airfoil profiles are used in compressor design, then the structure is simple and easy to manufacture, but the compression efficiency and energy performance are reduced
Solution Approach 1:
The patent applies parameter changes by optimizing the airfoil profile geometry through specific Cartesian coordinate values (X, Y, Z) that define the suction side, pressure side, and thickness distribution. These precise parameter specifications transform the conventional airfoil into an optimized profile that enhances compression efficiency while maintaining manufacturability through defined geometric parameters.
Solution Approach 2:
The patent implements local quality by optimizing specific portions of the airfoil profile independently - the suction side, pressure side, and thickness distribution are each defined with specific coordinate values tailored to their functional requirements. This localized optimization of different airfoil regions enables enhanced overall performance while addressing specific flow characteristics in different zones.
2Productivity
If optimized airfoil profiles with specific coordinate values are implemented, then compression efficiency and pressure ratios increase, but the design and manufacturing precision requirements increase
Solution Approach 1:
The patent specifies precise parameter changes through detailed Cartesian coordinate values for the airfoil profile, defining the suction side, pressure side, and thickness distribution with exact X, Y, Z coordinates. These parameter specifications enable optimized compression performance while providing clear manufacturing guidance through defined geometric parameters that can be precisely controlled during fabrication.
3Loss of energy
If conventional airfoil designs are used across multiple compressor stages, then the design is simple and consistent, but energy consumption increases and performance is reduced
Solution Approach 1:
The patent reduces energy losses by implementing parameter changes in the airfoil profile geometry, optimizing the suction side, pressure side, and thickness distribution through specific coordinate values. These parameter optimizations enhance compression efficiency and reduce energy consumption across multiple compressor stages by improving flow characteristics and reducing losses.
Solution Approach 2:
The patent addresses energy losses through local quality optimization of the airfoil profile, where specific portions of the airfoil (suction side, pressure side, thickness regions) are optimized with tailored coordinate values to minimize losses in critical flow areas while maintaining overall design consistency across compressor stages.
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
These optimized airfoil profiles improve the efficiency of gas compression, leading to increased energy levels and pressure ratios, reducing energy consumption and enhancing overall compressor performance.
Implementation Method 1
Airfoil shape for inlet guide vane of a 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.