Gas Turbine Blade With Varying Back Channel Density
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Solution Overview
Problem
Gas turbine blades face challenges in improving durability while minimizing the amount of cooling air used, as existing cooling methods are inefficient in effectively distributing and utilizing cooling air to manage high-temperature combustion gas flows.
Innovation Solution
The design incorporates a blade with a flow passage forming plate featuring varying densities of openings in different regions, optimizing cooling air distribution to enhance heat transfer coefficients where needed, and reducing the total flow rate of cooling air by strategically arranging back channels and blowout channels to effectively cool the blade surfaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If cooling channels are formed in the blade body to cool the blades, then the durability of the blades is improved, but the amount of cooling air required increases
Solution Approach 1:
The patent applies local quality by varying the density of back channel openings across different regions of the blade. The middle region (first region) has a higher density of openings compared to the suction-side region (second region) and pressure-side region (third region). This non-uniform distribution optimizes cooling air utilization by providing more cooling where the combustion gas flow velocity is higher and heat transfer coefficients are greater, thereby improving blade durability while minimizing the total amount of cooling air required.
2Temperature
If the density of back channel openings is increased in the middle region, then the cooling performance in high-heat areas is improved, but the complexity of the flow passage structure increases
Solution Approach 1:
The patent applies segmentation by dividing the blade's flow passage forming plate into three distinct regions: a middle region (first region) with high density of back channel openings, a suction-side region (second region) with lower density, and a pressure-side region (third region) with lower density. This segmentation allows optimized cooling air distribution to different thermal zones while maintaining a manageable structural complexity through systematic regional differentiation rather than entirely unique designs for each area.
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 approach enhances the cooling performance and durability of the blades by efficiently utilizing cooling air, reducing the amount required, and improving thermal efficiency in gas turbines.
Implementation Method 1
Both the stator blades and the rotor blades of the gas turbine are exposed to high-temperature combustion gas. Therefore, these stator blades and rotor blades are commonly cooled with air etc.
Implementation Method 2
various cooling channels through which cooling air passes are formed in the stator blade
Data Source
AI summary
A blade has a flow passage forming plate that defines a part of a combustion gas flow passage. The flow passage forming plate has a plurality of back channels that open in a back end surface. A density of openings of the plurality of back channels in a middle region of the back end surface is higher than the density of openings of the plurality of back channels in at least one side region of a suction-side region and a pressure-side region of the back end surface. The density of openings is a ratio of a length of wetted perimeter of the plurality of back channels to an interval of openings of the plurality of back channels.