Second Stage Compressor Rotor Blade Airfoil Profile Optimization
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Solution Overview
Problem
Current compressor designs for gas turbine engines face inefficiencies in multi-stage axial compressors due to suboptimal airfoil profiles, leading to inadequate compression and energy transfer in specific stages, particularly in the second stage, which affects overall system performance.
Innovation Solution
The development of airfoil profiles with specific Cartesian coordinate values for suction and pressure sides, optimized for specific velocities and turning speeds, which are convertible to dimensional distances, enhancing the efficiency and performance of compressor rotor blades and stator vanes across various stages.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional airfoil profiles are used in multi-stage axial compressors, then manufacturing and design are simpler, but compression efficiency and energy transfer are inadequate
Solution Approach 1:
The patent applies parameter changes by optimizing the airfoil profile through specific Cartesian coordinate values (X, Y, Z) that define the suction and pressure side geometries. These coordinate parameters are carefully selected to enhance compression efficiency and energy transfer characteristics in multi-stage axial compressors, particularly in the second stage where performance improvement is most critical.
Solution Approach 2:
The patent implements local quality by providing different airfoil profile configurations for different stages of the compressor. Specifically, the second stage rotor blade airfoil has optimized coordinates tailored for its specific operating conditions, while other stages may have different profiles. This allows each stage to be optimized locally for its specific flow and pressure conditions, maximizing overall compressor efficiency.
2Power
If airfoil profiles optimized for specific velocities and turning speeds are implemented, then energy transfer improves, but design and manufacturing complexity increases
Solution Approach 1:
The patent utilizes parameter changes by defining the airfoil geometry through specific Cartesian coordinate values that are optimized for particular velocity ranges and turning speeds. These coordinates (X, Y, Z) serve as design parameters that can be adjusted to match different operating conditions, allowing the airfoil to achieve optimal energy transfer performance for its intended application.
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.