Gas Turbine Airfoil Plenum and Flared Tip Design
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Solution Overview
Problem
Existing gas turbine engine airfoils face challenges in achieving a balance between low weight, high strength, and improved aerodynamic performance, particularly at the interface between the blade and shroud.
Innovation Solution
The airfoil design incorporates a flared portion along the suction surface sidewall and a plenum with a multi-segmented sidewall at the outer edge, along with cooling elements such as recesses and cooling holes, to enhance aerodynamic performance while reducing weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If the airfoil weight is reduced by hollowing out portions, then the weight decreases, but the strength and structural integrity deteriorate
Solution Approach 1:
The airfoil is divided into multiple functional segments: a solid root portion for structural strength, hollowed-out mid-sections for weight reduction, and a solid tip portion for aerodynamic performance. The plenum is segmented into multiple chambers that communicate through channels, allowing weight reduction while maintaining structural integrity through strategic reinforcement at critical locations.
Solution Approach 2:
Different portions of the airfoil have different structural qualities - the root and tip maintain solid construction for strength and aerodynamic stability, while the mid-section incorporates hollowed-out portions and plenums for weight reduction. The multi-segmented sidewall structure provides localized reinforcement where needed while maintaining overall weight reduction.
2Productivity
If the airfoil interface with shroud is optimized for aerodynamic performance, then the aerodynamic performance improves, but the complexity of the airfoil structure increases
Solution Approach 1:
The airfoil interface structure is segmented into multiple components: the main airfoil body, the plenum with multiple chambers, the multi-segmented sidewall structure, and integrated cooling elements. This segmentation allows each component to be optimized independently for aerodynamic performance while managing overall structural complexity through modular design.
Solution Approach 2:
The airfoil interface structure serves multiple functions simultaneously: it provides aerodynamic performance through optimized shaping, structural support through the multi-segmented sidewall, weight reduction through hollowed-out portions, and cooling through integrated cooling holes and recesses. This multi-functionality reduces the need for separate components and manages complexity through integration.
Data Source
AI summary
An airfoil for a turbine engine includes a body defining a pressure side and a suction side, the body extending between a leading edge and a trailing edge and also extending radially to define an outer edge. A radially-extending plenum can be disposed at the outer edge of the airfoil. A flared portion can be disposed at the outer edge of the body extending from the suction side.