Turbine Vane Aerodynamic Profile Optimization
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Solution Overview
Problem
The existing aerodynamic profiles for turbine vanes in gas turbines, particularly in the low-pressure turbine stages of aircraft turbojets, fail to optimize efficiency due to turbulence and mechanical stress issues, and are not easily manufacturable using casting techniques, leading to premature wear and inefficiency.
Innovation Solution
An optimized aerodynamic profile for a nozzle vane of a turbine, defined by Cartesian coordinates, which is substantially identical to a nominal profile with minor deviations, allowing for efficient air flow and stress distribution, and is adaptable to manufacturing tolerances and temperature variations, ensuring compatibility with casting techniques and improved mechanical resilience.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional aerodynamic profiles are used for turbine vanes, then manufacturing is simpler, but turbulence occurs reducing efficiency
Solution Approach 1:
The patent applies parameter changes by precisely defining the aerodynamic profile through specific Cartesian coordinates (X, Y, Z) that optimize airflow characteristics. The profile parameters including curvature radii (R1=50mm, R2=100mm, R3=75mm, R4=125mm) and coordinate points are carefully selected to minimize turbulence while remaining compatible with casting manufacturing processes, thus resolving the contradiction between efficiency and manufacturability.
2Productivity
If the profile is optimized for aerodynamics, then turbulence is reduced, but mechanical stress distribution worsens
Solution Approach 1:
The patent applies local quality by optimizing different regions of the vane profile with specific geometric characteristics. The aerodynamic surface has specific curvature radii (R1, R2 for the aerodynamic portion; R3, R4 for the transition portion) and coordinate points that are tailored to achieve both smooth airflow and even stress distribution. The transition portion specifically connects the aerodynamic and non-aerodynamic portions with optimized local geometry to balance aerodynamic performance and mechanical strength.
3Productivity
If the profile deviates from nominal dimensions, then aerodynamic performance improves, but manufacturing precision requirements worsen
Solution Approach 1:
The patent defines precise parameter values for the aerodynamic profile including specific coordinates and curvature radii that optimize aerodynamic performance. These parameters are selected to achieve the desired efficiency while remaining compatible with casting manufacturing capabilities, effectively balancing performance optimization with manufacturing precision requirements.
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,Z′ given in Table 1, in which the coordinate Z′ 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.