Dual Cut-Back Trailing Edge Cooling for Turbine Airfoils
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Solution Overview
Problem
Existing cooling designs for the trailing edge and pressure side lip of turbine engine airfoil components face challenges in balancing flow distribution due to sensitive aerodynamic wedge angles and casting tolerances, making it difficult to effectively cool these areas.
Innovation Solution
A dual cutback trailing edge cooling system is introduced, featuring a first cavity for cooling the trailing edge and a second cavity for the pressure side wall, with dedicated passageways and slots that allow for improved cooling fluid distribution and film coverage, potentially using ceramic or refractory metal cores for fabrication.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single cavity is used to cool both the trailing edge and pressure side lip, then the cooling system is simpler, but the flow distribution becomes difficult to balance due to sensitive aerodynamic wedge angles and casting tolerances
Solution Approach 1:
The single cooling cavity is divided into two separate cavities: a first cavity dedicated to cooling the trailing edge and a second cavity dedicated to cooling the pressure side lip. This segmentation allows independent flow control and eliminates the flow distribution balancing problems that occur when both areas are cooled from a single cavity.
2Area of stationary object
If aerodynamic wedge angles are increased to improve cooling coverage, then more areas are cooled, but aerodynamic efficiency decreases
Solution Approach 1:
The cooling system provides localized cooling with different wedge angles for different areas. The first cavity supplies cooling fluid to the trailing edge at specific angles, while the second cavity supplies cooling fluid to the pressure side lip at different angles. This allows each area to have optimized wedge angles for its specific cooling needs without compromising overall aerodynamic efficiency.
3Manufacturing precision
If cross-over hole geometry and drilling tolerances are tightened to improve flow balance, then cooling distribution improves, but manufacturing complexity and cost increase
Solution Approach 1:
By segmenting the cooling system into separate cavities for the trailing edge and pressure side lip, the design eliminates the need for precise cross-over hole geometry and drilling tolerances. Each cavity independently supplies cooling fluid to its designated area, removing the flow balance sensitivity to manufacturing variations that exists in integrated 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
This design achieves cooler trailing edge temperatures, allows for lower wedge angles for better aerodynamic efficiency, and minimizes backflow issues, enhancing film cooling effectiveness and coverage.
Implementation Method 1
The cooling air passes through a first row of cross-over holes and a second row of cross-over holes and finally into the cut back slot. The cavity between the rows of cross-over holes is also a source of cooling air for the pressure side of the airfoil portion via one or more rows of cooling film holes.
Implementation Method 2
The cooling system includes a first cavity dedicated to cooling a trailing edge portion of an airfoil portion and a second cavity dedicated to cooling an aft portion of a pressure side wall of the airfoil portion.
Data Source
AI summary
A cooling system for an airfoil portion of a turbine engine component is provided. The cooling system includes a first cavity dedicated to cooling a trailing edge portion of an airfoil portion and a second cavity dedicated to cooling an aft portion of a pressure side wall.