Turbine Blade Tip Shroud With Axially Offset Cutter Teeth
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Solution Overview
Problem
Turbine blade tip shrouds experience aerodynamic inefficiencies, imbalance, and reduced creep life due to interactions with stationary components, leading to performance losses and reliability issues.
Innovation Solution
The turbine blade tip shroud features axially offset cutter teeth and specific surface profiles defined by Cartesian coordinates, allowing for balanced and optimized aerodynamic interaction with stationary components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional tip shroud configuration is used, then manufacturing is simple, but aerodynamic performance is poor and creep life is reduced
Solution Approach 1:
The patent applies asymmetry by positioning cutter teeth at different axial locations on opposite sides of the tip rail. Specifically, a first cutter tooth is positioned at a first axial location and a second cutter tooth is positioned at a second axial location, creating an asymmetric configuration that balances aerodynamic forces while improving creep life. This asymmetric arrangement allows the tip shroud to interact more favorably with stationary components, reducing imbalance and extending service life.
2Reliability
If symmetric cutter teeth configuration is used, then manufacturing is easier, but aerodynamic imbalance occurs
Solution Approach 1:
The patent employs asymmetry by deliberately positioning cutter teeth at different axial locations rather than symmetrically. The first cutter tooth extends from a first axial location while the second cutter tooth extends from a second axial location, creating an asymmetric pattern that generates balanced aerodynamic forces during operation. This approach prioritizes aerodynamic balance over manufacturing simplicity.
3Productivity
If tip shroud interacts with stationary components, then aerodynamic function is achieved, but performance losses and imbalance occur
Solution Approach 1:
The patent applies local quality by modifying specific regions of the tip shroud through strategically positioned cutter teeth. The first and second cutter teeth are located at specific axial positions to create localized aerodynamic features that optimize the interaction with stationary components. This localized modification improves overall aerodynamic efficiency and reduces energy losses while maintaining the necessary interaction for energy conversion.
Data Source
AI summary
A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.