Turbine Rotor Blade Cooling Flow Path Segmentation
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Solution Overview
Problem
In power generation plants using supercritical carbon dioxide as a working fluid, the high heat transfer coefficient at turbine rotor blades necessitates efficient cooling while minimizing the supply flow rate of the cooling medium to maintain system efficiency.
Innovation Solution
The turbine rotor blade design incorporates multiple flow paths within the blade, snubber, platform, and implanted parts to efficiently distribute the cooling medium, allowing it to pass through various channels to cool these components effectively while reducing the overall supply flow rate.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the supply flow rate of cooling medium is increased to cool the rotor blade, then the cooling effect is improved, but the system efficiency deteriorates
Solution Approach 1:
The rotor blade is divided into multiple cooling regions (first cooling region, second cooling region, third cooling region) with different cooling requirements. Each region is equipped with dedicated cooling holes and flow paths, allowing targeted cooling without requiring high cooling medium flow rate across the entire blade. This segmentation enables effective cooling while minimizing overall cooling medium consumption.
Solution Approach 2:
Different portions of the rotor blade are provided with different cooling configurations based on their specific thermal conditions. The leading edge has first cooling holes, the rear surface has second cooling holes, and the tip has third cooling holes, each optimized for local heat transfer characteristics. This local quality approach ensures efficient cooling where needed while reducing unnecessary cooling elsewhere, thereby maintaining system efficiency.
2Temperature
If multiple cooling holes are provided in the rotor blade, then the cooling coverage is improved, but the device complexity increases
Solution Approach 1:
Multiple cooling functions are merged into a single integrated cooling system. The first cooling holes, second cooling holes, and third cooling holes are all connected through a unified cooling medium supply path and distribution network. This merging approach allows comprehensive cooling coverage while avoiding the complexity of separate independent cooling systems for each region.
Solution Approach 2:
The cooling medium supply system serves multiple functions simultaneously: it supplies cooling medium to the first cooling holes for leading edge cooling, to the second cooling holes for rear surface cooling, and to the third cooling holes for tip cooling. This multi-functionality reduces the need for separate cooling systems and minimizes overall device complexity while achieving broad cooling coverage.
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 design enhances cooling efficiency of the rotor blade and its components while minimizing the cooling medium supply flow rate, effectively managing thermal stress and maintaining system efficiency.
Implementation Method 1
the heat transfer coefficient at the blade surface of the rotor blade or the like becomes approximately 10 times compared to the conventional gas turbine
Data Source
AI summary
A turbine rotor blade comprises: a blade effective part; a snubber disposed on radially outer side of the blade effective part; a platform disposed on radially inner side of the blade effective part; and an implanted part disposed on radially inner side of the platform. A first flow path is formed inside the implanted part for a cooling medium to pass through. A second flow path is formed inside the platform for the cooling medium having passed through the first flow to pass through. A blade effective part flow path is formed inside the blade effective part for the cooling medium having passed through the second flow path to pass through. A snubber flow path is formed inside the snubber for the cooling medium having passed through the blade effective part flow paths to pass through.