Notched Turbine Vane Baffle for Trailing Edge Cooling
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Solution Overview
Problem
Existing turbine vane structures in gas turbine engines face challenges in effectively cooling the airfoil trailing edge due to the inefficiency of air cooling mechanisms, leading to potential overheating and reduced performance.
Innovation Solution
The introduction of a baffle with notches in the trailing edge, which fluidly couples an inner passage to an outer passage, allowing for improved air circulation and cooling by directing cooling air from the outer plenum into the trailing edge feed passage, thereby maintaining optimal temperature conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a baffle is introduced to direct cooling air to the trailing edge, then cooling efficiency is improved, but device complexity increases
Solution Approach 1:
The baffle is segmented with notches that divide the trailing edge region into multiple zones, allowing differentiated cooling airflow distribution. The notches segment the baffle structure into functional regions that direct cooling air to specific areas of the trailing edge, improving thermal management while maintaining a relatively simple overall baffle geometry.
Solution Approach 2:
The notched baffle acts as an intermediary component between the cooling air supply system and the trailing edge region. It mediates the airflow by directing cooling air from the inner passage through the notches to the outer passage, ensuring efficient heat removal without requiring complex additional cooling systems.
2Productivity
If notches are added to fluidly couple passages, then cooling air delivery is improved, but manufacturing complexity increases
Solution Approach 1:
The notches create a porous-like structure in the baffle, providing multiple flow paths for cooling air. This porous configuration allows efficient fluid coupling between the inner and outer passages while maintaining a simple geometric form that can be manufactured using conventional techniques such as machining or additive manufacturing.
Solution Approach 2:
The notches modify the geometric parameters of the baffle by creating openings with specific dimensions and arrangements. These parameter changes optimize the fluid flow characteristics, enabling effective cooling air delivery while the parameters are chosen to be compatible with standard manufacturing tolerances and processes.
3Reliability
If cooling air is directed to the trailing edge, then overheating is reduced, but energy consumption increases
Solution Approach 1:
The notched baffle performs preliminary action by directing cooling air to the trailing edge region before overheating can occur. The notches are positioned and sized to deliver cooling air proactively to high-temperature zones, preventing thermal damage and improving reliability without requiring excessive cooling air consumption.
Solution Approach 2:
The notches provide local quality enhancement by concentrating cooling air delivery at the trailing edge where it is most needed. The notches are strategically positioned to target specific high-temperature regions, ensuring efficient heat removal with minimal cooling air consumption rather than applying uniform cooling across the entire airfoil.
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 notched baffle design enhances cooling efficiency by delivering relatively cold cooling air to the trailing edge, reducing overheating and improving the performance and longevity of the turbine vanes.
Implementation Method 1
The notch fluidly couples the inner passage to the outer passage
Implementation Method 2
delivering relatively cold cooling air to the trailing edge
Data Source
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AI summary
An assembly for a turbine engine (22) includes an airfoil (82) and a baffle (84). A cavity (107) projects spanwise into the airfoil (82) from an airfoil tip end (88) towards an airfoil base end (86). The baffle (84) is disposed in the cavity (107) with an outer passage (126) formed between the baffle (84) and a wall (96A, 96B, 101) of the airfoil (82). An inner passage (154) projects spanwise into the baffle (84) from the baffle tip end (138) towards the baffle base end (136). A notch (156) is disposed in the baffle trailing edge (142) at the baffle base end (136). The notch (156) fluidly couples the inner passage (154) to the outer passage (126).