Turbine Vane Load Shield Cooling Air Distribution
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Solution Overview
Problem
Gas turbine engine vanes face challenges in withstanding high temperatures due to the interaction with combustion products, requiring high-temperature resistant materials and active cooling, which is complex in design and manufacture, especially with composite materials.
Innovation Solution
A turbine vane design incorporating a ceramic-containing web as the suction side and a metallic load shield as the pressure side, with a cooling channel between them, featuring multiple cooling air inlet ports and restrictor plates to dissipate heat effectively, and bleed holes for efficient cooling air distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If high-temperature resistant materials and active cooling are used, then temperature resistance is improved, but design and manufacture complexity increases
Solution Approach 1:
The patent applies composite materials by combining a ceramic-containing web (providing high-temperature resistance) with a metallic load shield (providing structural strength and cooling capability). This composite structure allows the vane to withstand high temperatures while the metallic portion can be manufactured with conventional techniques, reducing overall manufacturing complexity compared to using complex composite materials throughout the entire structure.
2Temperature
If cooling air is supplied to the vane, then temperature is reduced, but cooling air consumption increases
Solution Approach 1:
The cooling channel is positioned specifically between the ceramic-containing web and the metallic load shield, targeting the region of highest thermal stress. The ceramic material inherently provides thermal insulation, so cooling is concentrated only where the metallic load shield requires it, rather than cooling the entire vane structure. This localized cooling approach reduces the total quantity of cooling air needed while maintaining effective temperature control.
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
The design effectively manages high temperatures by distributing cooling air through the vane, reducing the need for extensive cooling air and enhancing durability, making it suitable for high-temperature gas turbine engine applications.
Implementation Method 1
The metallic load shield may include cooling features arranged in the first cooling air inlet port that increase surface area of the metallic load shield along the first cooling air inlet port so that heat is dissipated through the cooling features by cooling air flowing through the first cooling air inlet port
Implementation Method 2
The restrictor plate may be formed to include a first restriction port in fluid communication with the first cooling air inlet port and sized to cause a first pressure to be established within the first cooling air inlet port by cooling air supplied to the first cooling air inlet port
Data Source
AI summary
A turbine vane for use in a gas turbine engine is disclosed. The turbine vane includes an inner platform, an outer platform spaced from the inner platform, and an airfoil that extends from the inner platform to the outer platform. The airfoil includes a ceramic-containing web that forms a portion of the airfoil and a metallic load shield that forms another portion of the airfoil.