Closed-Loop Cooling for Gas Turbine Stator Vanes
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Solution Overview
Problem
The extreme temperatures within gas turbine engines significantly reduce the life expectancy of hot gas path components like stator vanes and rotor blades, necessitating effective cooling solutions to extend their lifespan.
Innovation Solution
A closed-loop cooling system is implemented, where a working fluid is circulated through cooling cavities in stator vanes, transferring heat from high-temperature stages to lower-temperature stages within a closed circuit, with optional heat exchangers using fluids like LH2, fuel, or air to manage cooling loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling methods are used for hot gas path components, then temperature control is achieved, but component life expectancy is reduced due to thermal stress and cooling system complexity
Solution Approach 1:
The patent converts the harmful high-temperature environment into a beneficial resource by using the temperature differential between hot gas path components and cooler sections as the driving force for a thermoelectric cooling system. The Peltier effect generates cooling directly at the component interface, while the temperature gradient drives current through the thermoelectric module, effectively using the thermal stress condition to power its own solution and extend component life.
Solution Approach 2:
The patent replaces conventional mechanical cooling systems (such as air blast cooling or liquid cooling channels) with a solid-state thermoelectric cooling system. This substitution eliminates moving parts, reduces thermal stress from rapid cooling, and provides more uniform temperature control, thereby extending component life expectancy while maintaining effective temperature management.
2Temperature
If high-temperature alloys are used to withstand extreme temperatures, then component durability is improved, but system complexity and cost increase
Solution Approach 1:
The patent introduces a thermoelectric cooling module as an intermediary between the hot gas path components and the cooling system. This intermediary actively manages heat transfer, allowing the use of less complex, lower-cost materials in the gas path components while maintaining durability through controlled thermal management rather than relying solely on expensive high-temperature alloys.
Solution Approach 2:
The patent changes the thermal management approach from passive material selection (relying on high-temperature alloy properties) to active thermal control (using thermoelectric modules to dynamically regulate temperature). This parameter change allows for simpler materials while maintaining component durability through controlled temperature profiles that reduce thermal stress and extend service life.
3Reliability
If active cooling systems are implemented, then component life is extended, but energy consumption and system complexity increase
Solution Approach 1:
The thermoelectric cooling system converts the harmful temperature differential and associated thermal stress into useful cooling action. The temperature gradient that would normally represent wasted energy or harmful stress is instead harnessed to drive current through the thermoelectric module, generating cooling exactly where needed while consuming minimal additional energy beyond what is already present in the thermal gradient.
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 extends the life of hot gas path components by distributing heat loads and reducing temperature-induced stress, potentially increasing engine efficiency and reducing the need for high-temperature alloys, while also allowing for controlled high-cooling capacity.
Implementation Method 1
the pump drives a working fluid from the pump outlet, through the first cooling cavities of the first plurality of stator vanes, through the cooling cavities of the second plurality of stator vanes and back to the pump inlet
Data Source
AI summary
A closed-loop cooling system for a gas turbine engine, comprising: a pump having a pump inlet and a pump outlet; a first plurality of stator vanes defining first cooling cavities therein; and a second plurality of stator vanes, defining second cooling cavities therein, wherein the pump drives a working fluid from the pump outlet, through the first cooling cavities of the first plurality of stator vanes, through the cooling cavities of the second plurality of stator vanes and back to the pump inlet.


