Segmented Cooling Trenches for Turbine Airfoil Leading Edge
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engines face challenges in effectively cooling airfoils due to uneven heat distribution, as existing cooling methods often fail to adequately manage the high heat loads along the leading edges, leading to potential damage from hot combustion gases.
Innovation Solution
The design incorporates multiple cooling trenches along the leading edge of airfoils, with cooling holes providing cooling air flows that create protective films on both the pressure and suction sides, with specific trench and hole configurations optimized to align with heat load zones and airfoil geometry.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling holes are provided on the leading edges of airfoils, then thermal protection is improved, but uneven heat distribution and inadequate cooling of high heat load zones occur
Solution Approach 1:
The leading edge cooling system is segmented into multiple cooling trenches (first cooling trench, second cooling trench, third cooling trench) positioned at different locations. Each trench receives cooling air through dedicated cooling holes, allowing independent control and optimization of cooling at each segment to match the local heat load distribution.
Solution Approach 2:
Different cooling trenches are positioned to address specific local heat load zones: the first cooling trench at the stagnation line for maximum heat load, the second cooling trench offset toward the pressure side, and the third cooling trench offset toward the suction side. This localizes cooling effectiveness to where it is most needed.
2Reliability
If multiple cooling trenches are added to manage heat loads, then cooling effectiveness is improved, but device complexity increases
Solution Approach 1:
Multiple cooling trenches are merged into a unified leading edge cooling structure that shares common cooling air supply pathways. The trenches are integrated along the span of the airfoil, allowing coordinated cooling action while reducing the number of separate cooling systems needed.
Solution Approach 2:
The cooling trenches serve multiple functions simultaneously: they provide thermal protection to the leading edge, manage uneven heat distribution across different zones, and protect both pressure and suction sides of the airfoil. This multi-functionality reduces the need for separate cooling systems for each purpose.
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 thermal protection by ensuring consistent cooling air films across the airfoil surfaces, effectively managing heat loads and extending the lifespan of turbine blades.
Implementation Method 1
The cooling air serves as a medium for heat transfer and can establish films of cooling air along the surfaces of the airfoil
Implementation Method 2
cooling air flows that create protective films on both the pressure and suction sides
Data Source
Figure 1
Figure 2
Figure 3
AI summary
Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil (112) includes: an exterior surface defining a leading edge (202), a trailing edge (204), a suction side (206) and a pressure side (208); an interior surface defining an interior cavity (261); trenches (214, 216, 218) in the exterior surface oriented spanwise along the leading edge (202); and cooling holes (220, 222, 224) communicating between the interior cavity (261) and the trenches (214, 216, 218) such that cooling air provided to the interior cavity flows from the interior cavity though the cooling holes into the trenches, the cooling holes (220, 222, 224) having exterior apertures (252) located in the trenches (214, 216, 218) and interior apertures (266) located at the interior surface.