Turbine Blade Aerodynamic Profile Optimization
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Solution Overview
Problem
Current turbine blade aerodynamic profiles fail to optimize efficiency and mechanical stress distribution, leading to turbulence and premature wear, especially under high temperature and dynamic loading conditions in gas turbines.
Innovation Solution
An optimized aerodynamic profile for turbine blades defined by specific Cartesian coordinates, allowing for slight deviations and rotations, which is designed to maintain efficiency and mechanical integrity across various operational conditions, including high temperatures and dynamic loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a conventional turbine blade profile is used, then the blade structure is simple and easy to manufacture, but aerodynamic efficiency is poor and turbulence occurs
Solution Approach 1:
The patent applies parameter changes by precisely adjusting the geometric parameters of the blade profile (coordinates X, Y, Z along the blade length) to optimize aerodynamic performance. The profile is defined by specific coordinate points that control the curvature and shape, transforming a simple profile into an optimized one through systematic parameter modification while maintaining manufacturability
Solution Approach 2:
The patent transitions from a two-dimensional cross-sectional view to a three-dimensional profile definition by specifying coordinates (X, Y, Z) along the blade length. This dimensional approach allows precise control of the blade's aerodynamic shape, enabling optimization of flow characteristics while accounting for the blade's longitudinal variation
2Productivity
If a conventional turbine blade profile is used, then the manufacturing process is simple, but turbulence occurs and efficiency is reduced
Solution Approach 1:
The optimized profile is defined by specific coordinate parameters (X, Y, Z) that can be directly input into manufacturing systems. By establishing precise mathematical definitions of the profile geometry, the patent enables modern manufacturing methods (CNC machining, additive manufacturing) to produce complex shapes with standard equipment, reconciling manufacturing simplicity with aerodynamic optimization
3Power
If the blade operates under high temperature and dynamic loading, then power output is maintained, but premature wear and stress concentration occur
Solution Approach 1:
The patent applies local quality by optimizing different sections of the blade profile independently. The coordinate system allows specific regions (root, mid-section, tip) to have tailored geometries that address local stress concentrations and thermal gradients. This localized optimization distributes mechanical stresses more evenly throughout the blade structure, preventing premature failure at critical locations while maintaining overall power output
Solution Approach 2:
The patent performs preliminary optimization of the blade profile geometry before manufacturing and operation. By pre-calculating and pre-defining the optimal coordinates that account for expected thermal and mechanical loads, the blade is designed to withstand high-temperature and dynamic loading conditions from the outset, preventing stress concentration and extending service life before installation
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
The optimized profile enhances aerodynamic efficiency, reduces turbulence, and effectively distributes mechanical stresses, leading to improved turbine performance and extended blade lifespan.
Implementation Method 1
the flow of air around the profile is sound, i.e. substantially such that it does not give rise to turbulence
Implementation Method 2
it does not give rise to turbulence, which is harmful for overall efficiency
Implementation Method 3
enabling it to withstand the mechanical stresses to which the blade is subjected, by enabling those stresses to be spread over the entire blade
Implementation Method 4
Since turbine blades are subjected to high temperature gradients, it is common practice for them to be provided with a coating having thermal properties enabling them more easily to withstand such temperature variations
Data Source
AI summary
When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.