Turbine Vane Non-Uniform Wall Cooling
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Solution Overview
Problem
Gas turbine engine turbine vanes face challenges in effectively managing high combustion gas temperatures, requiring improved cooling systems to prevent material failure and enhance performance.
Innovation Solution
The turbine vane features an internal cooling system within a non-uniform thickness outer wall, with thinner sections at high-temperature gradient areas and a linear outer surface, facilitating easier cooling and improved manufacturability of film cooling holes, while avoiding external tapering and aerodynamic complexities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the outer wall is made with uniform thickness, then manufacturing is simpler, but cooling efficiency at high-temperature gradient areas is insufficient
Solution Approach 1:
The outer wall thickness is varied locally to match thermal requirements: thinner at the leading edge where temperature gradients are highest to improve cooling efficiency, and thicker at the trailing edge and root areas where structural support is needed. This local differentiation resolves the contradiction by optimizing cooling where needed without compromising overall manufacturability.
2Temperature
If the outer wall is tapered externally, then cooling of leading edge is improved, but aerodynamic performance deteriorates and manufacturing complexity increases
Solution Approach 1:
Instead of tapering the outer surface (external taper), the patent inverts the approach by maintaining a linear outer surface and applying the taper internally to the inner wall. This internal tapering achieves the same cooling benefit at the leading edge while preserving the aerodynamic quality of the external surface and simplifying manufacturing.
3Ease of manufacture
If the outer surface is made nonlinear to accommodate internal cooling features, then cooling system integration is improved, but aerodynamic analysis becomes more complex
Solution Approach 1:
The patent applies the nonlinear geometry to the inner wall rather than the outer surface. This allows the internal cooling features (such as film cooling holes and diffuser sections) to be integrated more effectively into the wall structure, while the outer surface remains linear and aerodynamically simple for easier analysis.
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
This configuration enhances cooling efficiency, increases castability, simplifies aerodynamic analysis, and provides a safety feature in case of impingement insert failure, maintaining effective cooling and reducing manufacturing complexities.
Implementation Method 1
The airfoils include an internal cooling system for reducing the temperature of the airfoils
Implementation Method 2
The outer wall may be formed from a non-uniform thickness such that aspects of the vane that are susceptible to the largest temperature gradients within the vane
Data Source
AI summary
A turbine vane for a gas turbine engine having an outer wall of non-uniform thickness. The turbine vane may be formed from a generally elongated airfoil formed from an outer wall having a leading edge, a trailing edge, a pressure side, a suction side, a first endwall at a first end, a second endwall at a second end opposite the first end, and an internal cooling system positioned internally of the outer wall. The outer wall may be formed of a non-uniform thickness such that aspects of the outer wall positioned between an outboardmost portion of the outer wall and an inboardmost portion of the outer wall are thinner than the outboardmost and inboardmost portions of the outer wall.