Turbine Blade Cooling Structure for Thermal Stress Reduction
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Solution Overview
Problem
Conventional gas turbine blades are prone to damage due to increased thermal stress and heat load resulting from higher combustion gas temperatures, which limits their operational efficiency and lifespan.
Innovation Solution
A turbine blade design featuring internal cooling channels that circulate cooling air through the airfoil, with multiple channels guiding air to the leading edge, upper surface, and trailing edge, reducing thermal stress by dissipating heat effectively.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the temperature of combustion gas is increased to improve output power and efficiency, then the power and efficiency are improved, but the thermal stress and heat load on turbine blades increase causing damage risk
Solution Approach 1:
The turbine blade is divided into multiple functional zones with separate cooling channels: a first cooling channel for the leading edge, a second cooling channel for the upper surface, and a third cooling channel for the internal structure. This segmentation allows targeted cooling of different high-stress regions, enabling the blade to withstand higher combustion temperatures while maintaining durability.
Solution Approach 2:
The cooling channels are nested within the turbine blade structure itself. The first, second, and third cooling channels are integrated into the blade's internal architecture, with the third channel positioned between the first and second channels. This nesting allows the cooling system to be embedded within the blade without significantly increasing external dimensions, while providing comprehensive thermal protection.
2Reliability
If cooling channels are added to reduce thermal stress, then the thermal protection is improved, but the device complexity increases
Solution Approach 1:
Multiple cooling functions are merged into a unified cooling channel system. The first, second, and third cooling channels are integrated and interconnected, with the third channel serving as a bridge between the leading edge cooling and upper surface cooling systems. This merging reduces the number of independent cooling systems needed while achieving comprehensive thermal protection across the entire blade.
Solution Approach 2:
The third cooling channel serves multiple functions simultaneously: it cools the internal structure of the blade, connects the first and second cooling channels, and distributes cooling air throughout the blade assembly. This multi-functionality reduces the overall complexity by eliminating the need for separate dedicated channels for each function.
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 cooling structure effectively reduces thermal load on the turbine blade, preventing damage and extending its operational lifespan by maintaining lower temperatures through efficient heat exchange and air circulation.
Implementation Method 1
an internal cooling channel disposed between the suction-side and pressure-side surfaces of the airfoil and configured to pass the cooling air throughout the airfoil from the inlet to an ejection hole formed on an upper surface of the airfoil
Implementation Method 2
circulation of cooling air through the turbine blade
Data Source
AI summary
A turbine blade with a cooling structure includes a root member coupled to a turbine disk; an inlet formed in the root member to introduce cooling air to the turbine blade; an airfoil coupled to the root member, the airfoil having a suction-side surface and a pressure-side surface; and an internal cooling channel disposed between the suction-side and pressure-side surfaces of the airfoil and configured to pass the cooling air throughout the airfoil from the inlet to an ejection hole formed on an upper surface of the airfoil. The turbine blade may be included in a turbine of a gas turbine and is provided to blow air passing through the cooling channel toward a leading edge and an upper surface of the airfoil, thereby reducing heat load and thermal stress applied to the turbine blade and preventing the turbine blade from being damaged by the heat load or thermal stress.