Turbine Blade Phase-Change Cooling Without Wick Structures
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Solution Overview
Problem
Existing technologies fail to efficiently address the challenge of cooling turbine blades, particularly in the context of the technical problem of heat dissipation in gas turbines, leading to potential damage from thermal stress and corrosion.
Innovation Solution
A gas turbine design incorporating a heat transfer part with a centrifugal or gravitational fluid circulation system, utilizing a heat transfer part with sealed first and second heat transfer portions to efficiently dissipate heat through phase changes of operating fluids, eliminating the need for a wick structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional cooling methods (convection cooling, impingement cooling, air film cooling, transpiration cooling) are used to cool the blade, then the blade heat-resisting is improved, but the cooling efficiency is insufficient and the blade remains vulnerable to thermal stress and corrosion
Solution Approach 1:
The patent employs phase transition cooling where cooling fluid undergoes phase change (liquid to vapor) within the blade's cooling channels. This phase transition process absorbs significant heat from the blade, providing superior cooling efficiency compared to conventional convection-based methods. The phase change mechanism directly addresses the insufficient cooling efficiency while maintaining enhanced blade heat-resisting capability.
2Power
If the compression ratio and combustion gas temperature are increased to improve gas turbine efficiency, then the power output is improved, but the heat-resisting of the blade becomes insufficient leading to potential damage
Solution Approach 1:
The phase transition cooling system absorbs intense heat from the high-temperature combustion gases through the phase change of cooling fluid, effectively counteracting the thermal stress and corrosion caused by high operating temperatures. This enables the gas turbine to operate at higher compression ratios and temperatures without compromising blade integrity.
Solution Approach 2:
The cooling fluid acts as an intermediary substance that transfers heat away from the blade. By introducing this intermediate cooling medium that undergoes phase change, the system protects the blade from direct exposure to harmful thermal effects while maintaining high power output conditions.
3Reliability
If conventional cooling structures are used, then the blade can be cooled, but the structure is complex requiring additional components like wick structures for fluid circulation
Solution Approach 1:
The cooling system utilizes the centrifugal force generated by the rotating turbine itself to circulate the cooling fluid through the cooling channels. This self-service mechanism eliminates the need for external pumps or complex wick structures, reducing overall structural complexity while maintaining reliable blade cooling capability.
Solution Approach 2:
The cooling fluid circulation is dynamically driven by the rotational motion of the turbine, utilizing centrifugal force that varies with operating speed. This dynamic circulation mechanism adapts to different operating conditions without requiring complex mechanical circulation systems, simplifying the overall 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 system effectively cools the turbine blades by continuously circulating and phase-changing operating fluids, enhancing heat dissipation and reducing thermal stress and corrosion, thus improving the durability and efficiency of the gas turbine.
Implementation Method 1
as the hub rotates, the operating fluid in the heat transfer part is circulated due to the centrifugal force according to the rotation of the hub and the blade
Implementation Method 2
a phase of the operating fluid is changed to cool the air foil
Implementation Method 3
when the hub extends along a direction without the rotation, the operating fluid falls freely due to the gravity and is circulated
Data Source
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AI summary
A gas turbine includes a hub, a blade and a heat transfer part. The hub has a plurality of combining slits formed along an outer surface of the hub by a predetermined distance. The blade has a root having a first space, a platform having a second space connected to the first space, and an air foil having a third space connected to the second space. The root is combined with each of the combining slits. The platform is disposed over the root. The air foil is disposed over the platform.