Turbine Blade Aerodynamic Profile Geometry Optimization
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Turbine blades in high-pressure gas turbines face challenges in achieving optimal aerodynamic and mechanical performance due to turbulence, mechanical stress, and thermal integrity, particularly in aircraft turbojets, where efficiency and cooling are critical.
Innovation Solution
An optimized aerodynamic profile for turbine blades is defined using rectangular coordinates, with slight deviations from a nominal profile to accommodate manufacturing tolerances and temperature variations, ensuring efficient air flow and mechanical durability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If the aerodynamic profile is optimized for minimal turbulence, then aerodynamic efficiency is improved, but manufacturing precision requirements increase
Solution Approach 1:
The patent applies parameter changes by modifying the aerodynamic profile geometry parameters (curvature radii, chord lengths, thickness distributions) to achieve optimal flow characteristics. The profile incorporates specific geometric parameters that minimize turbulence while remaining manufacturable, balancing aerodynamic efficiency with manufacturing capabilities.
2Object-generated harmful factors
If the profile geometry is highly optimized for aerodynamic performance, then turbulence is reduced, but ease of manufacture decreases
Solution Approach 1:
The patent applies local quality by optimizing specific local regions of the profile (leading edge curvature, trailing edge geometry, thickness distribution at critical sections) while maintaining simpler geometries in less critical areas. This allows turbulence reduction at key locations without requiring complex manufacturing throughout the entire profile.
3Strength
If the profile is designed for high mechanical stress resistance, then blade strength is improved, but aerodynamic efficiency may be compromised
Solution Approach 1:
The patent applies composite materials by combining the aerodynamic profile with a cooling circuit structure integrated into the blade. This composite design allows the profile to maintain optimized aerodynamic geometry while the internal cooling structure provides mechanical strength and thermal management, resolving the conflict between aerodynamic efficiency and structural integrity.
4Temperature
If a cooling circuit is implanted in the blade, then thermal integrity is improved, but device complexity increases
Solution Approach 1:
The patent applies the nested doll principle by integrating the cooling circuit within the internal structure of the blade profile. The cooling channels are nested inside the blade thickness, allowing thermal management functionality to be incorporated without significantly increasing the external profile complexity or aerodynamic drag.
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 rectangular coordinates X,Y,Z′ given in Table 1, in which the X coordinate is measured in the axial direction of the turbine, and the Z′ coordinate is the quotient D/H, where D is the distance of the point in question from a reference plane P0 situated at the base of the nominal profile and H is the height of the profile measured from said reference plane to the tip of the blade, the measurements D and H being taken radially relative to the axis of the turbine.