Compressor Rotor Blade Airfoil Profile 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, leading to reduced performance and energy transfer across stages.
Innovation Solution
The development of specific airfoil profiles for compressor rotor blades and stator vanes, defined by Cartesian coordinate values, which optimize velocity matching and turning speeds for specific stages of multi-stage axial compressors, enhancing energy transfer and pressure increase.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional airfoil profiles are used in compressor rotor blades, then manufacturing and design are simpler, but compressor efficiency and energy transfer are reduced
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 geometric parameters of the blade. This allows the airfoil shape to be tuned for maximum efficiency in matching fluid flow conditions across compressor stages, directly improving compressor efficiency while maintaining manufacturability through defined coordinate specifications.
Solution Approach 2:
The patent implements local quality by optimizing specific portions of the airfoil profile (suction side, pressure side, leading edge, trailing edge) with tailored coordinate values. Each section of the airfoil is designed with specific geometric properties to handle local flow conditions, enabling enhanced energy transfer and pressure increase while keeping the overall design systematic and manufacturable.
2Power
If suboptimal airfoil profiles are used, then design and manufacturing are easier, but energy transfer and pressure increase are reduced
Solution Approach 1:
The patent optimizes energy transfer by changing the geometric parameters of the airfoil profile through precisely defined Cartesian coordinates. The specific X, Y, Z values are selected to maximize the matching of fluid flow conditions across compressor stages, thereby enhancing the power and energy transfer capability of the compressor while providing clear manufacturing specifications.
3Speed
If conventional airfoil designs are used, then manufacturing is simpler, but velocity matching and turning speeds are suboptimal
Solution Approach 1:
The patent optimizes turning speed and velocity matching by changing the airfoil geometric parameters through specifically defined Cartesian coordinate values. The profile shape is tuned to achieve optimal fluid flow turning angles and velocities across compressor stages, while the coordinates provide clear manufacturing guidance for achieving these performance targets.
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.