Turbine blade tip cooling hole arrangement

A turbine blade for a gas turbine engine includes a plurality of cooling holes positioned adjacent a tip of the turbine blade. The plurality of cooling holes are oriented at specific angles to produce film-cooling of the turbine blade tip to improve durability and performance of the turbine blade. F...

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Bibliographische Detailangaben
Hauptverfasser:	Calixtro, Carlos, Guo, Yanhu, Gonzalez, Nelson D
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A turbine blade for a gas turbine engine includes a plurality of cooling holes positioned adjacent a tip of the turbine blade. The plurality of cooling holes are oriented at specific angles to produce film-cooling of the turbine blade tip to improve durability and performance of the turbine blade. Further, the plurality of cooling holes are positioned at specific locations to improve film-cooling of the turbine blade while reducing negative impacts on performance of the turbine blade.