Turbine Blade Platform Cooling via Interconnected Passages
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Temperature mismatches between the airfoil and platform, and shank and platform in turbine blades lead to thermal stresses, oxidation, fatigue, and reduced lifespan due to high operating temperatures, necessitating improved cooling solutions.
Innovation Solution
A turbine blade cooling system with interconnected pressure and suction side passages and cooling cavities between adjacent blades, allowing a cooling medium to flow through both platforms for enhanced heat transfer and stress reduction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If higher combustion temperatures are used to increase system efficiency, then power output and efficiency improve, but thermal stresses, oxidation, fatigue, and creep deflection increase leading to reduced component lifetime
Solution Approach 1:
The cooling system is segmented into multiple independent cooling passages (pressure side passage, suction side passage, platform cooling cavity) that can be independently designed and optimized. Each passage serves a specific cooling function, allowing the system to manage thermal loads more effectively while maintaining high combustion temperatures for efficiency.
Solution Approach 2:
A cooling medium acts as an intermediary substance that transfers heat away from the turbine blade components. The cooling medium flows through the interconnected passages and cavities, absorbing thermal energy from the blade platform and airfoil, thereby protecting the components from direct exposure to high combustion temperatures while enabling efficient operation.
2Reliability
If cooling passages and cavities are added to reduce thermal stresses, then component lifetime improves, but device complexity increases
Solution Approach 1:
Multiple cooling functions are merged into an interconnected system where the pressure side passage, suction side passage, and platform cooling cavity form a unified cooling network. The cooling medium flows sequentially through these passages, combining multiple cooling actions into a single integrated system that reduces thermal stresses without requiring separate independent cooling systems for each component.
Solution Approach 2:
The cooling medium serves multiple functions simultaneously: it cools the pressure side of the platform, cools the suction side of the platform, and transfers heat through the airfoil. This multi-functional cooling approach reduces the need for separate cooling systems and minimizes overall device complexity while achieving comprehensive thermal management.
3Reliability
If cooling medium flow is increased to enhance heat transfer, then thermal stress reduction improves, but energy consumption increases
Solution Approach 1:
The cooling system applies local quality by directing cooling medium flow to specific high-temperature regions where thermal stresses are most critical. The pressure side passage and suction side passage are positioned to target specific areas on the blade platform, and the platform cooling cavity focuses cooling on the most vulnerable regions. This localized cooling approach reduces the total energy required compared to uniform cooling of the entire blade.
Solution Approach 2:
The cooling medium flows continuously through the interconnected passages and cavities, maintaining constant heat transfer without interruption. The continuous flow ensures sustained cooling of the blade platform during operation, reducing thermal stresses over time while using energy efficiently through maintained flow rather than intermittent high-flow pulses.
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 enables higher combustion temperatures, increased efficiency, and extended component lifetime by effectively managing thermal stresses and enhancing heat transfer between adjacent turbine blades.
Implementation Method 1
flowing a cooling medium through a pressure side passage of a first turbine blade platform, flowing the cooling medium through a suction side passage of a second turbine blade platform, flowing the cooling medium through a platform cooling cavity in the second turbine blade platform
Implementation Method 2
cooling the second turbine blade platform
Data Source
AI summary
The present application provides a turbine blade cooling system. The turbine blade cooling system may include a first turbine blade with a first turbine blade platform having a cooling cavity in communication with a pressure side passage and a second turbine blade with a second turbine blade platform having a platform cooling cavity with a suction side passage. The pressure side passage of the first turbine blade platform is in communication with the suction side passage of the second turbine blade platform.