Gas Turbine Blade Cooling Core Merging Strategy
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Solution Overview
Problem
Gas turbine engine blades, particularly airfoil platforms, face challenges in cooling efficiency due to mixing losses and susceptibility to breakage during the casting process, leading to reduced engine performance and increased part costs.
Innovation Solution
The design incorporates a core structure with inlet passages that split into branches forming a triangular shape, providing a network of cooling passages within the blade, including serpentine passages and film cooling holes, which are formed using a ceramic core manufacturing process without glue, ensuring structural integrity and efficient cooling fluid distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a separate platform core is glued into a slot of a main core to provide cooling passages, then cooling efficiency is improved, but the platform core is susceptible to breakage during casting and manufacturing complexity increases
Solution Approach 1:
The patent merges the platform core and main core into a single integrated core structure. The cooling passages are formed by configuring the core itself with internal channels that extend through the platform region, eliminating the need for separate glued-in platform cores. This integration reduces manufacturing complexity while maintaining cooling efficiency.
2Device complexity
If multiple cores are glued together to form complex cooling passages, then cooling network complexity is improved, but structural integrity deteriorates due to glue joints
Solution Approach 1:
The patent combines multiple core functions into a single monolithic core structure. The cooling passages are formed within this unified core, eliminating weak glue joints between separate cores. The core is configured with internal channels that provide the required cooling network complexity while maintaining structural integrity throughout the entire assembly.
3Temperature
If film cooling holes are provided in the platform to improve cooling, then cooling efficiency is improved, but mixing losses increase and engine performance deteriorates
Solution Approach 1:
The patent applies local quality by providing cooling functionality specifically where needed through the core-configured passages that deliver coolant to the platform region and airfoil surfaces. Rather than using film cooling holes that inject coolant directly into the flow path causing mixing losses, the system uses localized cooling passages within the core structure to cool critical areas without disrupting the main gas flow.
4Volume of moving object
If the platform core is made thin to fit within platform boundaries, then spatial constraints are satisfied, but susceptibility to breakage increases and manufacturing yield deteriorates
Solution Approach 1:
By integrating the platform core with the main core into a single structure, the patent eliminates the need for a thin, fragile platform core. The unified core can be made with adequate thickness and strength to withstand casting processes, while the cooling passages are configured within this more robust structure. This integration significantly improves manufacturing yield and reliability.
Data Source
Figure 1
Figure 2A~2B
Figure 3A~3E
AI summary
A gas turbine engine blade includes a platform arranged between a root and an airfoil. A cooling passage extends from the root through the platform to the airfoil. The cooling passage includes an inlet that splits into first and second branches that rejoin one another in a platform passage arranged in the platform. An airfoil passage extends from the platform passage and is arranged in the platform.