Turbine Component Cooling via Closed-Loop Internal Channels
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Solution Overview
Problem
Current heat removal systems for turbines, while effective, do not adequately address the increased erosion, creep, and low cycle fatigue issues associated with higher operating temperatures along the hot gas path, and there is a need for an improved method to manage heat without introducing aerodynamic mixing losses.
Innovation Solution
A closed-loop cooling system with fluid channels embedded in or surrounded by coatings on turbine components, allowing a cooling media to flow through these channels from a supply plenum to a return plenum without exhausting into the hot gas path, providing conductive and convective cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If film cooling is used to cool turbine components, then cooling effectiveness is improved, but aerodynamic mixing losses increase
Solution Approach 1:
The invention extracts the cooling function from the hot gas path by implementing a closed-loop cooling system where cooling media circulate through internal cavities and passages without being exhausted into the hot gas path, thereby eliminating aerodynamic mixing losses while maintaining cooling effectiveness
Solution Approach 2:
The invention introduces a separate cooling media (intermediary substance) that circulates through the turbine components via internal cavities and passages, transferring heat away from the components without mixing with the hot gas path, thus avoiding the aerodynamic losses associated with film cooling
2Power
If higher operating temperatures are used in the turbine, then thermodynamic efficiency and power output are improved, but erosion, creep, and low cycle fatigue increase
Solution Approach 1:
The invention segments the thermal management function by separating the hot gas path from the cooling function, with dedicated internal cavities and passages for cooling media circulation, allowing the turbine components to operate at high temperatures while maintaining structural integrity through effective heat removal
Solution Approach 2:
The invention implements preliminary cooling action by circulating cooling media through internal cavities before the hot gas path components are exposed to extreme temperatures, pre-cooling the components and preventing thermal damage that would lead to erosion, creep, and fatigue
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 system effectively removes heat from turbine components without the aerodynamic losses of film cooling, allowing higher operating temperatures while reducing the amount of cooling media required and enabling heat retention or recapture, thus enhancing overall efficiency.
Implementation Method 1
A first fluid channel is between the outer surface of the substrate and the exterior surface of the coating
Implementation Method 2
circulate a cooling media through internal cavities in the components to provide convective and conductive cooling to the components
Data Source
AI summary
A system for removing heat from a turbine includes a component in the turbine having a supply plenum and a return plenum therein. A substrate that defines a shape of the component has an inner surface and an outer surface. A coating applied to the outer surface of the substrate has an interior surface facing the outer surface of the substrate and an exterior surface opposed to the interior surface. A first fluid channel is between the outer surface of the substrate and the exterior surface of the coating. A first fluid path is from the supply plenum, through the substrate, and into the first fluid channel, and a second fluid path is from the first fluid channel, through the substrate, and into the return plenum.