Turbine Blade Assemblies With Segmented Cooling Conduits for 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 potential creep and fatigue issues that can result in premature part replacement.
Innovation Solution
The development of blade assemblies with optimized cooling conduit geometries, including variations in the middle inlet passage shape and size, to enhance cooling efficiency and improve creep and fatigue resistance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling conduits are added to turbine blades, then cooling efficiency is improved, but device complexity increases
Solution Approach 1:
The cooling conduits are nested within the blade structure itself, with multiple conduits arranged in a serpentine pattern through the blade thickness. The conduits are integrated into the blade's internal geometry, allowing cooling functionality to be embedded without adding external components.
Solution Approach 2:
The cooling system is divided into multiple separate conduits rather than a single large channel. The blade contains several cooling conduits with different orientations and locations, allowing distributed cooling across the blade surface and improving overall cooling efficiency.
2Reliability
If cooling conduits are added to turbine blades, then creep and fatigue resistance is improved, but manufacturing complexity increases
Solution Approach 1:
The manufacturing process parameters are changed to accommodate the cooling conduits. The patent specifies particular conduit geometries, wall thicknesses, and material properties that optimize both cooling performance and manufacturability. The conduits are designed with specific dimensional parameters that balance cooling efficiency with manufacturing constraints.
Solution Approach 2:
Traditional mechanical drilling or machining of cooling holes is replaced with additive manufacturing technology. The serpentine cooling conduits are directly formed during the blade manufacturing process using additive methods, eliminating the need for complex post-processing operations and reducing manufacturing complexity.
3Temperature
If middle inlet passage geometry is optimized, then cooling efficiency is improved, but manufacturing precision requirements increase
Solution Approach 1:
The middle inlet passage is designed with specific geometric parameters including particular curvature radii, cross-sectional areas, and angles that optimize cooling flow distribution. These parameters are carefully selected to achieve efficient cooling while remaining manufacturable with standard precision capabilities.
Solution Approach 2:
Additive manufacturing technology is used to create the middle inlet passage geometry, replacing traditional CNC machining or drilling processes. This substitution allows for complex curved geometries and precise dimensional control that would be difficult or expensive to achieve with conventional mechanical manufacturing methods.
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 optimized blade assemblies demonstrate enhanced durability and reduced creep and fatigue, thereby increasing the time between maintenance and replacement, while maintaining performance within engine constraints.
Implementation Method 1
a first cooling conduit portion at a first plane radially spaced 0.0167 meters from the base plane, the first cooling conduit portion having a first cross-sectional area
Implementation Method 2
The optimized blade assemblies demonstrate enhanced durability and reduced creep and fatigue, thereby increasing the time between maintenance and replacement
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.