Gas Turbine Platform Cooling Augmentation
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engine components, such as blades and vanes, face challenges in withstanding high temperatures due to lack of effective cooling methods that efficiently manage heat transfer without requiring large flow pressure ratios.
Innovation Solution
Incorporating augmentation features like trip strips, pin fins, and chevron trip strips on the outer surfaces of platforms within the gas turbine engine, which enhance heat transfer by turbulating the leakage airflow and increasing surface area, thereby cooling the components effectively.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If dedicated cooling airflow is communicated to components, then cooling effectiveness is improved, but flow pressure ratio requirements increase
Solution Approach 1:
The patent applies local quality by placing specific augmentation features (trip strips, pin fins, chevrons) at critical locations on the platform surface where heat transfer is most needed. These features create localized turbulence and enhance convective heat transfer coefficients at the leading edge and other high-heat-flux regions, improving cooling effectiveness without requiring increased overall flow pressure ratio
Solution Approach 2:
The patent utilizes fluid dynamics principles by introducing surface features that manipulate the boundary layer and induce turbulence in the cooling airflow. The trip strips and pin fins disrupt laminar flow to create turbulent flow patterns that enhance mixing and heat transfer, while chevrons create vortex structures that improve convective cooling efficiency without requiring higher pressure ratios
2Reliability
If platform cooling is enhanced, then component thermal resistance is improved, but device complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the platform surface into distinct zones with different augmentation features. Trip strips are placed at the leading edge, pin fins are positioned in specific patterns, and chevrons are located at trailing edges or high-heat-flux regions. This segmented approach allows each feature type to address specific thermal challenges, improving overall thermal resistance while maintaining manageable structural complexity through modular feature placement
Solution Approach 2:
The patent transitions from two-dimensional flat platform surfaces to three-dimensional augmented surfaces by adding vertical elements (pin fins extending perpendicular to the surface) and angled features (trip strips and chevrons with specific orientations). This dimensional enhancement increases the effective heat transfer surface area and creates complex flow patterns that improve thermal resistance without requiring additional cooling systems
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 described solution effectively cools gas turbine engine components by improving heat transfer efficiency without the need for large flow pressure ratios, enhancing their ability to withstand high temperatures and reducing mixing losses.
Implementation Method 1
enhance heat transfer by turbulating the leakage airflow
Implementation Method 2
enhance heat transfer by turbulating the leakage airflow and increasing surface area
Data Source
AI summary
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least the leading edge portion or the trailing edge portion of the outer surface of the platform.