Baffle Insert Vortex Cooling for Turbine Airfoils
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engine airfoil sections, particularly those downstream of the combustor, face high thermal and mechanical loads due to high combustion temperatures, leading to reduced service life and increased maintenance costs, necessitating effective cooling techniques.
Innovation Solution
The use of baffle inserts with trip strips and separating features within internal cooling cavities of airfoil components to create vortices in the cooling fluid, enhancing convective cooling by increasing heat transfer coefficients and reducing operational temperatures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If high combustion temperatures are used to increase power output, then power and energy efficiency are improved, but thermal loads on turbine airfoils increase reducing service life and reliability
Solution Approach 1:
The internal cooling cavity is segmented into multiple flow regions by the baffle insert with trip strips, creating distinct zones that facilitate vortex formation and enhance heat transfer throughout the cooling passage
Solution Approach 2:
The baffle insert acts as an intermediary element within the cooling cavity, mediating the flow of cooling fluid to create vortices that improve heat transfer between the hot airfoil walls and the cooling fluid
2Temperature
If conventional cooling methods are used, then some cooling effect is achieved, but heat transfer efficiency is insufficient requiring more cooling fluid
Solution Approach 1:
The trip strips create mechanical disturbances in the cooling fluid flow, generating vortices that enhance mixing and heat transfer efficiency, thereby reducing the quantity of cooling fluid needed to achieve the desired temperature control
Solution Approach 2:
The baffle insert changes the flow parameters of the cooling fluid by inducing vortices and turbulence, transforming the flow regime to achieve higher heat transfer coefficients with reduced fluid quantity
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 increases heat transfer efficiency, reduces cooling fluid requirements, and extends the service life of airfoil components while minimizing stress concentrations and operational costs.
Implementation Method 1
creating a plurality of vortices in the cooling fluid as it passes between the exterior surface of the baffle insert and the interior surface of the internal cooling cavity
Implementation Method 2
directing a cooling fluid between an interior surface of an internal cooling cavity of the component and an exterior surface of a baffle insert located in the internal cooling cavity
Data Source
Figure 1
Figure 2A~2B
Figure 3~4
AI summary
A method of increasing a heat transfer of a cooling fluid passing through a component of a gas turbine engine. The method including the steps of: directing a cooling fluid between an interior surface (36) of an internal cooling cavity (26) of the component and an exterior surface of a baffle insert (32) located in the internal cooling cavity; and creating a plurality of vortices in the cooling fluid as it passes between the exterior surface of the baffle insert and the interior surface of the internal cooling cavity, wherein the internal cooling cavity is elliptical in shape and/or wherein the exterior surface of the baffle insert is elliptical in shape.