Partial Ribs in Turbine Airfoil Cooling Chambers
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Solution Overview
Problem
Large tip airfoils in gas turbine engines face structural challenges such as bulge and panel vibration due to their configuration, and existing cooling systems may not effectively distribute cooling flow to manage heat loads and prevent these issues.
Innovation Solution
The use of partial ribs within the cooling chamber of airfoils, which provide structural support and optimize the distribution of cooling flow, reducing bulge and vibration while enhancing heat transfer efficiency by positioning ribs strategically and using elliptical fillets to smooth airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If full-length ribs are used in large tip airfoils, then structural support is improved, but panel bulge and vibration increase due to improper cooling flow distribution
Solution Approach 1:
The patent divides the full-length rib structure into multiple partial ribs that extend only along portions of the airfoil span. This segmentation allows each partial rib to be strategically positioned to provide structural support where needed while avoiding areas where they would interfere with cooling flow distribution, thereby reducing panel bulge and vibration.
Solution Approach 2:
The patent applies different rib configurations at different locations along the airfoil span. Partial ribs are strategically positioned to provide local structural reinforcement in high-stress areas while leaving other areas open for optimal cooling flow distribution, creating a non-uniform structure that addresses local requirements rather than applying a uniform solution throughout.
2Temperature
If cooling channels are added to manage heat loads, then thermal management is improved, but device complexity increases
Solution Approach 1:
The partial ribs serve multiple functions simultaneously: they provide structural support to the airfoil, act as flow distributors to optimize cooling air distribution, and serve as structural integrators that connect various airfoil components. This multi-functionality reduces the need for separate dedicated cooling components, thereby managing heat loads without proportionally increasing device complexity.
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 implementation of partial ribs in airfoils effectively reduces panel bulge and vibration, improves cooling flow distribution, and enhances heat transfer capabilities, allowing for more balanced air speeds and reduced thermal loads on the airfoil.
Implementation Method 1
cooling channels are typically defined by support ribs in an internal chamber of the airfoil... create flow channels within the hollow volume of the airfoil that are fed with cooling air to cool the airfoil
Implementation Method 2
The rib may include an elliptical fillet at its end that receives the onboard cooling airflow... elliptical fillets to smooth airflow
Implementation Method 3
optimize the distribution of cooling flow... enhances heat transfer efficiency by positioning ribs strategically
Data Source
Figure 1
Figure 2A
Figure 2B
AI summary
In various embodiments, an airfoil (270; 370) used as a turbine blade for a turbine wheel in a gas turbine engine (120) is provided. The airfoil (270; 370) may comprise a root (274), a tip (272), and a body. The root (274) may have a first area. The tip (272) may have a second area. The body may have a chord (278) bounded by the root (274) and the tip (272). The body may also define a cooling chamber (276). The cooling chamber (276) may have a first rib (280) substantially perpendicular to the chord (278). The cooling chamber (276) may also have a second rib (282) extending partially between the root (274) and the tip (272).