| 摘要 |
The invention relates to a turbine blade ( 31 ) having a root region ( 33 ), a tip region ( 37 ) and a blade airfoil ( 35 ), a rounded portion ( 73 ) being formed between the root region ( 33 ) and the blade airfoil ( 35 ), and relief slots ( 51 ) passing through the blade trailing edge ( 41 ) in the region of this rounded portion ( 73 ), thermal expansions being compensated for and thus thermal stresses being minimized by these relief slots ( 51 ).
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