Trenched Cooling Holes for Ceramic Matrix Composite Vane
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Solution Overview
Problem
Current cooling arrangements for high-temperature components in gas turbine engines face limitations, particularly in gas path flow disruption and material constraints, necessitating a more effective cooling solution for airfoil-shaped components.
Innovation Solution
A unique cooling arrangement featuring trenched cooling holes on the surface of high-temperature components, including airfoil-shaped components in gas turbine engines, where the cooling holes have variable geometry and are integrated with a composite structure, such as ceramic matrix composites, to efficiently supply a cooling fluid and reduce thermal gradients while maintaining structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional cooling arrangements are used for high-temperature components, then cooling is provided to some extent, but gas path flow disruption occurs and material constraints limit effectiveness
Solution Approach 1:
The patent applies local quality by implementing trenched cooling holes with specific geometries (e.g., angled trenches, varied depths) at different locations on the airfoil surface. Each trench is strategically positioned and shaped to provide localized cooling where thermal loads are highest, while the trench configuration minimizes interference with the overall gas path flow compared to traditional uniform cooling holes
Solution Approach 2:
The patent transitions from conventional point-based cooling holes to three-dimensional trenched structures. The trenches extend into the material with specific depths, angles, and cross-sectional shapes, adding dimensional complexity to the cooling feature geometry. This dimensional enhancement allows for greater cooling surface area and improved thermal management while maintaining a more aerodynamically integrated profile
2Temperature
If cooling holes are added to high-temperature components, then cooling efficiency improves, but structural integrity may be compromised
Solution Approach 1:
The patent employs ceramic matrix composite (CMC) materials for the airfoil structure. CMCs provide exceptional high-temperature strength, thermal resistance, and structural integrity even with the presence of cooling trenches. The composite structure allows for the integration of complex trench geometries while maintaining strength-to-weight ratios and structural performance at elevated temperatures
Solution Approach 2:
The cooling system is segmented into multiple discrete trenches with varying geometries rather than using a single large cooling feature or numerous small holes. This segmentation allows the cooling function to be distributed throughout the airfoil structure, reducing thermal gradients and stress concentrations while preserving structural continuity and integrity
3Temperature
If more coolant flow is used to improve cooling, then temperature control improves, but coolant flow requirements increase
Solution Approach 1:
The patent optimizes cooling performance by carefully controlling trench parameters including depth, width, angle, and distribution patterns. By adjusting these geometric parameters, the system achieves effective temperature control with minimized coolant consumption. The trench configurations are designed to maximize cooling efficiency per unit of coolant flow, reducing the overall quantity of coolant required compared to traditional cooling arrangements
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 enhances cooling efficiency by forming a stronger cooling fluid film, reduces coolant flow requirements, and increases adiabatic effectiveness at the trailing edge without compromising structural integrity, addressing the limitations of existing cooling methods.
Implementation Method 1
cooling holes have variable geometry and are integrated with a composite structure, such as ceramic matrix composites, to efficiently supply a cooling fluid and reduce thermal gradients
Implementation Method 2
The solution enhances cooling efficiency by forming a stronger cooling fluid film
Data Source
AI summary
One aspect of the present application provides an apparatus comprising a shape operable as a gas turbine engine component, an internal cavity within the shape including a radius, a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity, and a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component.