Gas Turbine Cooling Circuit Layout for Higher Thermal Loads
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Solution Overview
Problem
Existing cooling technologies for gas turbine engine components, such as turbine blades and vanes, are limited in their ability to withstand high thermal loads due to constraints in cooling capacity provided by refractory metal cores.
Innovation Solution
The implementation of diverging and converging cooling circuits with pedestals and flow directing features that enhance turbulence and convective heat transfer, allowing for improved cooling coverage and thermal management of components like blades, vanes, and combustor panels.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If refractory metal cores are used to create cooling circuits just under the surface of the hot wall, then cooling capacity is improved, but the temperature the component can withstand is still limited
Solution Approach 1:
The cooling circuit is divided into multiple segments including an impingement section with multiple cooling holes arranged in a circular pattern, a transition section, and a diverging section. This segmentation allows different sections to perform specialized functions - the impingement section creates intense localized cooling, the transition section manages flow expansion, and the diverging section distributes coolant across the surface, collectively enhancing both cooling capacity and temperature resistance
Solution Approach 2:
The cooling system implements local quality by concentrating cooling resources in the impingement section where multiple jets directly impinge on the hot wall surface, creating zones of enhanced heat transfer. The diverging section then distributes the cooled fluid across broader areas. This localized intensification followed by distribution allows the component to withstand higher temperatures at critical locations while maintaining overall thermal management
2Productivity
If cooling circuits are placed just under the surface through refractory metal cores, then specific cooling passages are increased, but the amount of cooling provided is still limited
Solution Approach 1:
The invention transitions from traditional linear cooling passages to a three-dimensional cooling architecture featuring a circular array of impingement holes arranged in multiple rows. This spatial dimensionality change allows coolant to be delivered to multiple locations simultaneously and creates volumetric cooling zones rather than surface-level cooling only, significantly increasing total cooling capacity while maintaining high density of cooling passages
Solution Approach 2:
The system utilizes hydraulic principles by employing high-velocity coolant jets that impinge directly on the hot wall surface through multiple small holes. The kinetic energy of the jets creates forced convection and enhances heat transfer coefficients dramatically. The diverging section then uses pressure-driven flow to distribute the coolant across the component surface, maximizing the effectiveness of each unit of cooling fluid and increasing overall cooling capacity
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
Enhances the thermal efficiency and durability of gas turbine engine components by increasing cooling capacity and maintaining effective temperature resistance.
Implementation Method 1
cooling circuits within the components... cooling air flows and is expelled into the gas path
Implementation Method 2
pedestals and flow directing features that enhance turbulence and convective heat transfer
Data Source
Figure 1
Figure 2
Figure 3~6
AI summary
A component for a gas turbine engine (20) includes a wall portion that includes an interior surface and an exterior surface. At least one cooling circuit (100D) is defined by the wall portion and includes a plurality of pedestals (132) that extend across the cooling circuit (100D). A width of the cooling circuit (100D) increases in a downstream direction. At least one cooling fluid inlet (128) extends through the interior surface and is in fluid communication with the cooling circuit (100D). At least one cooling fluid outlet (130) extends through the exterior surface and is in fluid communication with the cooling circuit (100D).