| 摘要 |
A turbine blade for a gas turbine engine with a tip rail that forms a gap between the blade and the turbine shroud, where the tip rail is located near to the suction side wall of the blade and offset there from, and where the tip rail includes sidewalls that are slanted inward from top to bottom to form a vortex pocket on the sides of the tip rail. Film cooling holes open out into the vortex pockets on both sides of the tip rail to supply cooling air. Film cooling holes located on the upstream side of the squealer tip and on the pressure side wall of the blade force the hot gas leakage flow to flow over the squealer tip while the cooling air in the vortex pockets flows in a vortex flow pattern to force the hot gas leakage flow off of the rail tip and further toward the blade outer air seal. The leakage flow past the tip rail forms a vortex flow path downstream of the tip rail on the airfoil suction side wall while the cooling air forms a counter vortex flow within the vortex pockets to trap the flow within the vortex pocket, resulting in a longer duration of time in which the flow occurs in the pockets for cooling of the tip rail.
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