ROTOR BLADE AND GAS TURBINE PROVIDED THEREWITH
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United States of America
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Issued Date -
Jan 30, 2025
app pub date -
Sep 26, 2022
filing date -
Sep 26, 2022
priority date (Note) -
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status (Latency Note)
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Abstract
A rotor blade including: a blade body extending in a blade height direction that is a direction perpendicular to an airfoil cross-section; and a platform provided to an end at a hub side, from between a tip side and the hub side which are of the blade height direction. The blade body includes: an anterior edge and a posterior edge; a ventral surface and a dorsal surface linking the anterior edge and the posterior edge together; and a cooling passage extending in the blade height direction between the ventral surface and the dorsal surface. The ventral/dorsal wall thickness ratio at any position between the hub-side position and the middle position in the cooling passage is smaller than the ventral/dorsal wall thickness ratio at any position between the middle position and the tip-side position.
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