Turbine Vane Airfoil Geometry Optimization
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Solution Overview
Problem
Gas turbine engine turbine vanes face design challenges in meeting multi-disciplinary requirements for performance and life due to complex boundary conditions, particularly in high-temperature environments where traditional designs may not adequately mitigate detrimental temperature effects.
Innovation Solution
The design incorporates a turbine vane with airfoils defined by Cartesian coordinates, forming a doublet vane structure with a first and second airfoil extending radially from an inner to an outer platform, and utilizing a set of coordinates with specified offsets to optimize the airfoil surface geometry, allowing for manufacturing tolerances and integration of cooling features.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional airfoil designs are used in high-temperature environments, then manufacturing and design simplicity is maintained, but performance and life are insufficient due to detrimental temperature effects
Solution Approach 1:
The patent applies parameter changes by precisely controlling the airfoil geometry through Cartesian coordinates with specified tolerances (±0.020 inches). The airfoil shape parameters including thickness distribution, camber, and leading/trailing edge configurations are optimized to withstand high-temperature environments while maintaining manufacturing feasibility through defined coordinate systems and tolerance specifications.
2Object-affected harmful factors
If complex cooling features are integrated into the turbine vane, then high-temperature stress management is improved, but manufacturing complexity increases
Solution Approach 1:
The patent applies segmentation by integrating cooling features as distinct functional elements within the turbine vane structure. The cooling features including internal passages and surface cooling structures are designed as separate geometric entities that can be manufactured and assembled, allowing complex thermal management functionality to be achieved while maintaining reasonable manufacturing processes through modular feature integration.
3Productivity
If precise Cartesian coordinates with tight tolerances are used to define airfoil geometry, then aerodynamic performance is optimized, but manufacturing precision requirements increase
Solution Approach 1:
The patent optimizes aerodynamic efficiency through precise parameter definition using Cartesian coordinates with a tolerance of ±0.020 inches. The coordinate system origin is strategically positioned at the trailing edge intersection with the inner platform, and key geometric parameters including airfoil thickness, camber line, and surface contours are precisely controlled within this tolerance band to achieve optimal aerodynamic performance while maintaining manufacturing feasibility.
Data Source
AI summary
A turbine vane for a gas turbine engine, including: a first airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from an inner platform in a radial direction to an outer platform, wherein a portion of the exterior airfoil surface of the first airfoil is formed in conformance with a set of Cartesian coordinates set forth in Table 1 as offset by corresponding values in Table 4, and wherein the values of Table 4 are offset from a point of origin that is a point where a radially outward surface of the inner platform meets a surface of a trailing edge of the inner platform and a surface of a mate face of the inner platform.