Airfoil Cooling Conduit Geometry for Turbine Blade Durability
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Solution Overview
Problem
Gas turbine engines experience significant thermal and mechanical stresses, particularly in high-pressure turbine stages, leading to premature part failure due to creep and fatigue, necessitating improved durability and stress management in blade assemblies.
Innovation Solution
The blade assembly incorporates a design with varied conduit sizing and geometry, including cooling conduits and inlet passages, to enhance durability by controlling cooling fluid distribution and stress redistribution, while maintaining operational constraints.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling conduits are added to the blade assembly, then temperature control is improved, but device complexity increases
Solution Approach 1:
The cooling conduits are nested within the blade assembly structure itself, with inlet passages positioned in the shank and cooling holes in the airfoil, creating a hierarchical arrangement where cooling channels are embedded inside the blade components without adding external complexity
Solution Approach 2:
The blade assembly incorporates multiple cooling holes that create a porous-like structure in the airfoil, allowing cooling fluid to pass through and distribute thermal management throughout the blade interior while maintaining structural integrity
2Strength
If varied conduit sizing is implemented, then stress distribution is improved, but manufacturing precision requirements increase
Solution Approach 1:
The cooling conduits feature varied cross-sectional areas at different locations along their length, with larger openings in regions experiencing higher thermal and mechanical stresses, providing localized stress relief and improved creep resistance where most needed while maintaining standard manufacturing tolerances
3Temperature
If more cooling conduits are added, then cooling effectiveness is improved, but weight increases
Solution Approach 1:
The blade assembly includes a selective arrangement of cooling holes and conduits concentrated in the airfoil region experiencing highest thermal loads, providing sufficient cooling effectiveness without the excessive weight penalty of uniform cooling throughout the entire blade structure
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 improves creep and fatigue resistance, extending the engine's Time on Wing (TOW) by ensuring adequate cooling and load-bearing capabilities under extreme temperature and rotational conditions.
Implementation Method 1
a plurality of cooling conduits located within the airfoil... to enhance durability by controlling cooling fluid distribution
Data Source
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AI summary
A gas turbine engine having a blade assembly (30) with a platform (50) , an airfoil (60) , and a shank (40) . The airfoil (60) has a plurality of cooling conduits, and the shank (40) has a plurality of inlet passages (48) to provide cooling fluid to the cooling conduits in the airfoil. The cooling fluid is vented through a plurality of cooling holes (69) along the airfoil. The blade assembly (30) has specific geometries that improve durability.