Gas Turbine Rotor Blade Weight Reduction via Truss Aperture
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Solution Overview
Problem
Gas turbine rotor blades face challenges in reducing weight while maintaining structural integrity, particularly in the attachment region where mass is required to prevent fracture under centrifugal and airfoil bending loads.
Innovation Solution
The rotor blade design incorporates a truss shape defined by a platform section, internal airfoil cooling passage, and underplatform fillet, with a weight reduction feature that includes an aperture or dimple in the neck section, allowing for material removal within this truss area to reduce weight without compromising structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If material is removed from the blade to reduce weight, then blade weight decreases, but structural integrity and strength may be compromised
Solution Approach 1:
The patent introduces an aperture (hole) through the blade structure, creating a porous or hollow configuration. This removes material to reduce weight while the surrounding truss structure maintains structural integrity. The aperture allows weight reduction without completely compromising the blade's strength characteristics.
Solution Approach 2:
The patent creates a composite truss structure combining the platform section, internal airfoil cooling passage, and underplatform fillet. This composite configuration forms a load-bearing framework that can sustain mechanical loads while accommodating material removal for weight reduction.
2Weight of moving object
If material is removed from the attachment region, then blade weight decreases, but fracture resistance under centrifugal loads deteriorates
Solution Approach 1:
The patent applies local quality by concentrating material in specific critical regions (platform section, underplatform fillet, and cooling passage walls) while removing material from less critical areas. The aperture is strategically positioned and sized to reduce weight while preserving material where it is most needed for fracture resistance under centrifugal loading.
Solution Approach 2:
The patent utilizes curved geometry in the underplatform fillet and the circular aperture configuration. These curved features help distribute stresses more evenly around the aperture, preventing stress concentration that could lead to fracture under centrifugal loads, thereby maintaining reliability while reducing weight.
Data Source
AI summary
A rotor blade for a gas turbine engine having an edge buttress having an aperture. A method of reducing rotor blade weight includes removing material from within a truss area bounded by a platform section, an internal airfoil cooling passage, and an underplatform fillet.