Fifth Stage Compressor Rotor Airfoil Profile
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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 the fifth stage of multi-stage axial compressors, which affect overall system performance and energy transfer.
Innovation Solution
The development of specific airfoil profiles for compressor rotor blades and stator vanes, defined by Cartesian coordinate values, that optimize velocity matching and turning speeds for each stage, including the fifth stage, to enhance compression efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional airfoil profiles are used in the fifth stage compressor, then the design is simpler and easier to manufacture, but the compression efficiency and energy transfer are suboptimal
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 and pressure side contours. These precise geometric parameters are tailored for the fifth stage compressor to maximize compression efficiency and energy transfer, transforming the conventional generic profile into a stage-specific optimized design.
Solution Approach 2:
The patent implements local quality by designing a customized airfoil profile specifically for the fifth stage compressor, rather than using a uniform design across all stages. The coordinate values are locally optimized for this particular stage's flow conditions, velocity matching requirements, and turning speed characteristics, making each part of the compressor system have the specific properties needed for its function.
2Productivity
If optimized airfoil profiles with specific coordinate values are implemented, then velocity matching and turning speeds are improved, but the manufacturing precision requirements increase
Solution Approach 1:
The patent specifies precise parameter changes through detailed Cartesian coordinate values (X, Y, Z) that define the airfoil geometry to three decimal places. These parameters are optimized for velocity matching and turning speed in the fifth stage, achieving superior energy transfer efficiency while providing clear manufacturing specifications.
Solution Approach 2:
The patent replaces traditional empirical or approximate airfoil design methods with a systematic coordinate-based definition system. By using explicit Cartesian coordinates to define the airfoil profile, the design transitions from mechanical trial-and-error approaches to a precision-defined geometric system that can be accurately manufactured and replicated.
3Power
If the airfoil profile is optimized for fifth stage specific conditions, then stage performance increases, but the overall compressor design complexity increases
Solution Approach 1:
The patent applies local quality by designing a specialized airfoil profile specifically for the fifth stage compressor conditions, optimizing it for the unique flow characteristics, velocity matching requirements, and pressure gain objectives of this particular stage. This localized optimization increases stage performance while maintaining clarity in the design specification through coordinate-based definition.
Solution Approach 2:
The patent implements parameter changes by adjusting the airfoil geometry parameters (Cartesian coordinates X, Y, Z) to match the specific operating conditions of the fifth stage. These parameter adjustments maximize pressure gain and energy transfer at this critical stage, with the coordinated design approach helping to manage overall system complexity.
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.