Nozzle segment for turbine engines

Nozzle segment for turbine engines

A nozzle singlet (32) for a turbine engine (10) is provided. The nozzle singlet (32) includes an inner band (40), an outer band (38), and at least one airfoil (36) extending therebetween, at least one first row (100) of cooling holes (60) oriented an angle with respect to at least one second row (11...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: HEFFRON, TODD S, GUENTERT, JOSEPH M, HEYWARD, JOHN
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 nozzle singlet (32) for a turbine engine (10) is provided. The nozzle singlet (32) includes an inner band (40), an outer band (38), and at least one airfoil (36) extending therebetween, at least one first row (100) of cooling holes (60) oriented an angle with respect to at least one second row (110) of cooling holes (120), wherein the orientation of the at least one first row and the at least one second row provides a cooling hole pattern that accommodates a change in an airfoil angle without reorienting the cooling hole pattern.