Third Stage Compressor Rotor Airfoil Shape Optimization
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Solution Overview
Problem
Current compressor designs for gas turbine engines face inefficiencies in compressing gases due to suboptimal airfoil profiles, particularly in specific stages of multi-stage axial compressors, which affect the overall performance and efficiency of the system.
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 conventional airfoil profiles are used in multi-stage axial compressors, then the design is simpler and easier to manufacture, but the compression efficiency and energy transfer performance deteriorate
Solution Approach 1:
The patent applies parameter changes by providing specific Cartesian coordinate values (X, Y, Z) that define the optimized airfoil profile geometry. The table of coordinate values represents precise dimensional parameters that differ from conventional profiles, enabling improved compression efficiency through modified airfoil shape parameters while maintaining manufacturability through defined numerical specifications.
2Power
If optimized airfoil profiles with specific coordinate values are implemented, then energy transfer and pressure increase improve, but the manufacturing precision requirements increase
Solution Approach 1:
The patent specifies precise Cartesian coordinate values in a table format that define the airfoil profile geometry. These parameter changes provide exact dimensional specifications (X, Y, Z coordinates) that enable improved energy transfer performance while establishing clear manufacturing targets. The non-dimensionalized coordinates with specified precision (e.g., three decimal places) balance performance optimization with manufacturability.
3Productivity
If stage-specific airfoil profiles are used, then compression performance at specific stages improves, but the design adaptability across different compressor configurations decreases
Solution Approach 1:
The patent applies local quality by providing specific airfoil profile coordinate values optimized for particular compressor stages (e.g., third stage rotor blades). The table of X, Y, Z coordinates defines stage-specific geometry that tailors the airfoil shape to the local flow conditions and performance requirements of specific compressor stages, thereby improving compression performance at those stages while acknowledging stage-specific design needs.
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 compression efficiency and operational performance of the compressor, leading to better energy transfer and pressure increase in the gas turbine system.
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... the airfoil sections of the nominal airfoil profile are coupled together to define an entirety of the airfoil
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.