Turbine Vane Insert Flow Discourager Thermal Gradient
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engine components, such as turbine vanes, face reduced service life due to high thermal gradients between the hot gas path and cooling airflow, which limits the use of high-temperature materials with reduced allowable stresses.
Innovation Solution
A turbine vane assembly with a vane insert and flow discourager is used to redirect and retain cooling airflow, reducing thermal gradients by preventing airflow past internal vane ribs, allowing for the use of high-temperature materials like ceramic matrix composites.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If high-temperature materials are used to increase exposure temperature, then temperature capability is improved, but allowable stress deteriorates
Solution Approach 1:
The turbine vane is divided into multiple segments including a skin, internal ribs, and an insert with flow discourager. This segmentation allows different regions to serve different functions: the skin exposed to hot gases uses high-temperature materials, while the insert and ribs manage cooling airflow to reduce thermal gradients and maintain structural integrity
Solution Approach 2:
The insert with flow discourager acts as an intermediary element between the hot gas path and the cooling airflow. It redirects the cooling airflow to prevent it from passing directly over the internal ribs, thereby reducing thermal gradients and allowing the use of high-temperature materials in critical areas without compromising stress resistance
2Duration of action of stationary object
If cooling airflow is increased to extend service life, then thermal stress is reduced, but device complexity increases
Solution Approach 1:
The cooling system is made dynamic through the movable flow discourager element within the insert. The flow discourager can be positioned or adjusted to optimize cooling airflow distribution, allowing the system to adapt to different thermal conditions without requiring a completely complex fixed structure
Solution Approach 2:
The insert with flow discourager utilizes the existing cooling airflow to achieve its function of reducing thermal gradients. The cooling air that would otherwise pass directly over the ribs is redirected by the flow discourager, making the system self-regulating without requiring additional active control mechanisms
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 gradients, enabling the use of high-temperature materials and extending the service life of turbine vanes by maintaining the temperature of internal vane ribs and reducing thermal stress.
Implementation Method 1
A turbine vane assembly with a vane insert and flow discourager is used to redirect and retain cooling airflow
Implementation Method 2
reducing thermal gradients by preventing airflow past internal vane ribs
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
An internally cooled component for a gas turbine engine (20) includes a component having one or more exterior walls defining an internal component cavity (98) configured for a cooling airflow (82) to flow therethrough. An internal component rib (96) extends into the internal component cavity from the one or more exterior walls. An insert (100) is positioned in the internal component cavity, and a flow discourager (102) is positioned at the insert and is configured to prevent the cooling airflow from flowing past the internal component rib.