Turbine Vane Platform Cooling via Segmented Ceramic Cores
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Solution Overview
Problem
Turbine vane platform cooling in gas turbine engines faces challenges in predicting practical results due to non-linear flow analyses and complex strain modeling, with design limitations imposed by vane loading and temperature considerations, making it difficult to generalize designs effectively across systems.
Innovation Solution
The use of ceramic core structures forming serpentine-like cooling passages within the vane platforms, with inner and outer platform cores arranged to prevent the core from passing beneath the airfoil, enhancing cooling efficiency and stress resistance while maintaining compactness and power density.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If non-linear flow analyses and complex strain modeling are used to achieve desired platform cooling results, then cooling effectiveness is improved, but design complexity and difficulty in predicting practical results increase
Solution Approach 1:
The cooling system is divided into distinct segments: a platform core structure with cooling passages, an airfoil mounted on the platform, and the core deliberately positioned to not extend beneath significant portions of the airfoil. This segmentation allows simplified analysis of each component while maintaining overall cooling effectiveness.
Solution Approach 2:
The core structure is strategically positioned to provide cooling primarily to the platform region, with the deliberate design choice that the core does not pass beneath significant portions of the airfoil. This localized cooling approach matches the thermal requirements of different regions, providing effective cooling where needed while simplifying the overall design analysis.
2Ease of manufacture
If the core is contained in the portion of the platform aft of the airfoil such that the core does not pass beneath any significant portion of the airfoil's other cooling passages, then manufacturing and analysis are simplified, but cooling coverage is reduced
Solution Approach 1:
The cooling system utilizes multiple spatial dimensions and layers: the platform core provides cooling in the platform region, while the airfoil contains its own separate cooling passages. This multi-layered, multi-dimensional cooling architecture ensures comprehensive coverage without requiring the core to extend beneath the airfoil, thereby maintaining manufacturing simplicity.
Solution Approach 2:
The cooling function is segmented between the platform core (for platform cooling) and the airfoil cooling passages (for airfoil cooling). This functional segmentation allows each component to be optimized independently for its specific cooling requirements while maintaining overall system simplicity and manufacturability.
3Reliability
If vane loading and temperature considerations are taken into account, then design reliability is improved, but design flexibility and generalizability are reduced
Solution Approach 1:
The turbine vane design incorporates a universal platform core configuration that can be applied across different turbine engine applications. The core structure with its specific positioning (not extending beneath significant portions of the airfoil) serves as a generalizable solution that addresses both platform cooling and airfoil cooling requirements, making the design adaptable to various vane loading and temperature conditions without requiring extensive redesign.
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 improves cooling efficiency, stress resistance, and compactness of turbine vanes, allowing for increased power density and reduced losses, while complex strain modeling is mitigated through optimized cooling passage designs.
Implementation Method 1
The platform cooling passages may be provided by flat, serpentine-like ceramic core structures arranged within the platforms
Implementation Method 2
The platform cooling passages are intended to protect the vane platform from the hot combustion gases
Data Source
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AI summary
A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.