Turbine Disk Pinned Platform Thermal Management
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Solution Overview
Problem
Designing ceramic matrix composite blades for gas turbine engines that can withstand high temperatures while minimizing thermal transfer and manufacturing complexity, particularly in creating a root, platform, and airfoil structure.
Innovation Solution
A blade assembly comprising a ceramic matrix composite blade, a separate ceramic matrix composite platform, and a pin that couples the platform with the blade, forming a flow path around the airfoil to guide hot gases and minimize thermal transfer, with the platform and blade being independent components and the pin located in passageways within both to secure them.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ceramic matrix composite materials are used for blades to withstand high temperatures, then temperature resistance is improved, but manufacturing complexity increases
Solution Approach 1:
The blade assembly is divided into separate components: the blade itself, the platform, and the pin. This segmentation allows each component to be manufactured independently using ceramic matrix composite materials, simplifying the overall manufacturing process while maintaining high temperature resistance capabilities.
Solution Approach 2:
The pin acts as an intermediary component that couples the platform to the blade. This intermediary approach allows for simplified assembly and manufacturing of the ceramic matrix composite structure, as the pin provides a straightforward mechanical connection method.
2Object-affected harmful factors
If a separate platform is used to guide hot gases and minimize thermal transfer, then thermal transfer is reduced, but device complexity increases
Solution Approach 1:
The platform is designed as a separate, segmented component that can be independently optimized for thermal management. This segmentation allows the platform to effectively guide hot gases and minimize thermal transfer to the blade root without requiring complex integrated designs.
Solution Approach 2:
The platform serves multiple functions: it guides hot gases around the airfoil, minimizes thermal transfer to the root, and provides structural support. This multi-functionality reduces the need for additional components, thereby managing device complexity while achieving thermal protection.
3Ease of manufacture
If the platform and blade are kept as independent components, then manufacturing is simplified, but connection reliability may be compromised
Solution Approach 1:
The pin serves as a reliable intermediary that securely couples the independent platform and blade components. This intermediary connection method maintains component independence for manufacturing simplicity while ensuring robust mechanical attachment for connection reliability.
Solution Approach 2:
The connection function is extracted into a separate pin component rather than being integrated into the blade or platform. This extraction allows the blade and platform to remain simple, independently manufacturable components while the dedicated pin ensures reliable connection.
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 solution effectively reduces thermal transfer to the blade root, enhances durability by using ceramic matrix composites, and simplifies manufacturing by keeping the platform and blade separate, thus improving the blade's ability to withstand high temperatures and reduce stress.
Implementation Method 1
The platform may be formed to include a second passageway that extends through the platform. The pin is located in the second passageway and the first passageway to couple the platform with the blade.
Data Source
AI summary
A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.