TIP SHROUD WITH EXIT SURFACE FOR COOLING PASSAGES

A tip shroud (220) for a turbine blade (114) of a GT system (100) may include a body (240) coupled to a radial outer end (222) of an airfoil (202) of the turbine blade (114). The tip shroud (220) may include at least one circumferentially extending tip rail (250). A first edge wall (252) of the tip...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	ZEMITIS, William Scott, BALKCUM III, James Tyson
Format:	Patent
Sprache:	eng ; fre ; ger
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 tip shroud (220) for a turbine blade (114) of a GT system (100) may include a body (240) coupled to a radial outer end (222) of an airfoil (202) of the turbine blade (114). The tip shroud (220) may include at least one circumferentially extending tip rail (250). A first edge wall (252) of the tip shroud (220) extends axially and radially outwardly from the body (240) along at least one of a leading circumferential-facing edge (234) or a trailing circumferential-facing edge (236) of the body (240), and includes a circumferentially facing surface (253). Cooling passages (246) are defined in the body (240) and extend circumferentially therein to cool an area near the first edge wall (252). The tip shroud (220) includes an exit surface (270) adjacent the first edge wall (252), where the exit surface (270) includes an exit opening (272) through which at least one of cooling passages (246) exits the body (240). The exit surface (270) is angled relative to the circumferentially facing surface (253) of the first edge wall (252) in a range of 15° to 80°.