Turbine Blade Partition Reduces Recirculation Losses
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Solution Overview
Problem
Existing turbine designs face challenges with air recirculation from the intrados to the extrados area, which leads to aerodynamic losses and reduces turbine efficiency.
Innovation Solution
The design incorporates a partition extending radially outward and axially between the attack edge and the upstream end of the platform, and between the leakage edge and the downstream end of the platform, to obstruct air recirculation and reduce the axial dimension of the external platform.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If the radially outer platform is reduced in axial dimension to lighten the blade, then the blade mass is reduced, but air recirculation from intrados to extrados increases causing aerodynamic losses
Solution Approach 1:
The radially outer platform is segmented into two distinct axial levels: a first axial level containing the leading edge and trailing edge, and a second axial level containing the upstream and downstream ends. This segmentation allows the platform to be reduced in axial dimension while maintaining the necessary sealing function through the lips at the second axial level, thereby reducing blade mass without increasing air recirculation losses
Solution Approach 2:
Lips extending radially outward at the second axial level serve as intermediary elements that seal between the radially outer platform and the abradable material. These lips prevent air recirculation through the gap created by the reduced platform dimension, allowing the platform to be lighter while maintaining aerodynamic efficiency
2Weight of moving object
If openings are formed in the radially outer platform to lighten the blade, then blade mass is reduced, but air flow is diverted from intrados to extrados creating recirculation
Solution Approach 1:
Instead of forming openings in the platform, the invention segments the platform axially into two levels with lips at the elevated second level. This segmentation provides an alternative weight reduction approach that does not compromise the sealing function, thereby maintaining turbine efficiency while reducing blade mass
Solution Approach 2:
The sealing function is moved from the radial dimension (openings in platform) to the axial dimension (elevated lips at second axial level). By utilizing the axial elevation to position lips above the abradable material, the invention achieves weight reduction without creating recirculation paths that would reduce turbine productivity
Data Source
Figure 1~2
Figure 3A~4B
AI summary
The invention relates to a turbine blade (13) for a turbomachine, comprising a turbine blade airfoil (14) extending radially, said turbine blade airfoil (14) having a leading edge (16) axially upstream and a trailing edge axially downstream, a radially outer platform (15) having an upstream end (17) and a downstream end, said radially outer platform (15) further comprising at least one lip (18, 19) extending radially towards the outside, the radially outer end (20) of the leading edge (16) of the turbine blade airfoil (14) and/or of the trailing edge of the turbine blade airfoil (14) extending axially upstream in relation to the upstream end (17) of the platform (15) and/or, respectively, extending downstream in relation to the downstream end of the platform (15), characterized in that the blade (13) has at least one partition (21) extending radially towards the outside from the radially outer end of the turbine blade airfoil (14) and axially between the leading edge (16) and the upstream end (17) of the platform (15) and/or, respectively, between the trailing edge and the downstream end of the platform (15).