Gas Turbine Blade Rib Transition Design
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Solution Overview
Problem
Gas turbine engine blades face challenges in designing efficient cooling systems due to differing thermal expansion requirements between airfoil and attachment ribs, leading to obstacles in providing effective cooling airflow.
Innovation Solution
The design incorporates a set of intersecting ribs with varying cross-sectional geometries transitioning from an airfoil to an attachment section, featuring distinct radial airfoil and attachment cross-sectional geometries, which define different cavities to manage thermal expansion and stiffness, ensuring efficient cooling airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If ribs are designed for airfoil flexibility to account for thermal expansion of outer walls, then thermal flexibility is improved, but structural strength at attachment is insufficient
Solution Approach 1:
The rib structure transitions from a flexible configuration in the airfoil section to a stiff configuration in the attachment section. This is achieved by varying the rib geometry along its length, with the rib being more compliant near the airfoil to accommodate thermal expansion and more rigid near the attachment to provide structural support and prevent crushing.
2Strength
If ribs are designed for attachment stiffness to prevent rib and attachment crushing, then structural strength is improved, but thermal flexibility of airfoil is reduced
Solution Approach 1:
The rib structure transitions from a flexible configuration in the airfoil section to a stiff configuration in the attachment section. This is achieved by varying the rib geometry along its length, with the rib being more compliant near the airfoil to accommodate thermal expansion and more rigid near the attachment to provide structural support and prevent crushing.
3Ease of manufacture
If a single rib geometry is used throughout the blade, then manufacturing complexity is reduced, but performance is compromised due to inability to satisfy both thermal expansion and stiffness requirements
Solution Approach 1:
The rib geometry parameters are varied continuously or in stages along the length of the rib, transitioning from the airfoil section to the attachment section. This allows the rib to provide appropriate flexibility or stiffness at different locations, optimizing both thermal management and structural performance without requiring multiple discrete rib components.
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 design enhances the structural integrity of the attachment while allowing for thermal flexibility of the airfoil, effectively managing thermal loads and preventing rib and attachment crushing, thereby improving the operational life of gas turbine engine blades.
Implementation Method 1
internal ribs or walls that form internal cavities through which a cooling airflow may flow from attachments coupled to the airfoils
Implementation Method 2
Because the outer walls are exposed to relatively hot air, they may experience greater thermal expansion than the internal ribs or walls
Data Source
AI summary
A blade for use with a gas turbine engine includes an attachment and an airfoil. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of intersecting ribs transitioning from an airfoil cross sectional geometry to an attachment cross section geometry.