Ninth Stage Compressor Rotor Airfoil Shape Optimization
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Solution Overview
Problem
Current compressor designs for gas turbine engines face inefficiencies in pressure and temperature increase across stages, particularly in the ninth stage of multi-stage axial compressors, due to suboptimal airfoil profiles that do not fully utilize specific velocities and turning speeds.
Innovation Solution
The development of airfoil profiles for compressor rotor blades and stator vanes with specific Cartesian coordinate values that define suction and pressure side surfaces, optimized for the ninth stage of a 14-stage axial compressor, enhancing energy transfer and compression efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional airfoil profiles are used in the ninth stage compressor, then the design is simple and manufacturing is easier, but compression efficiency and energy transfer are insufficient
Solution Approach 1:
The patent applies parameter changes by precisely defining the airfoil profile using specific Cartesian coordinate values (X, Y, Z) that optimize the geometry for ninth stage compression. The detailed coordinate specifications transform the airfoil parameters to achieve superior compression efficiency and energy transfer while maintaining manufacturability through defined geometric parameters.
2Use of energy by moving object
If optimized airfoil profiles with specific coordinate values are implemented, then energy transfer and compression efficiency improve, but manufacturing precision requirements increase
Solution Approach 1:
The patent defines specific Cartesian coordinate values (X, Y, Z) with precision to three decimal places, transforming the airfoil geometry parameters to optimize energy transfer efficiency. This parameter specification approach balances manufacturing precision requirements with performance optimization by providing exact geometric definitions.
3Productivity
If the airfoil suction portion is optimized to specific length ratios, then compression performance improves, but the design complexity increases
Solution Approach 1:
The patent optimizes the suction portion length to be less than or equal to the airfoil length with specific coordinate definitions, changing the geometric parameters to improve compression performance. The defined ratio relationships and coordinate specifications provide a systematic approach to optimizing performance while managing design complexity.
Data Source
AI summary
A system is provided, including an airfoil. The an 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.