| 摘要 |
The present application further describes a turbine blade that may include an airfoil a tip shroud that is positioned at one end of the turbine blade, a coolant passage that extends through the airfoil to the tip shroud, and a continuous cooling cavity that is defined within the tip shroud and that is in fluid communication with the coolant passage. The continuous cooling cavity may form a labyrinth cooling circuit within the tip shroud.
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