GAS TURBINE ENGINE AIRFOIL

A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil (78) extends from the radially outer side of the platform. The airfoil (78) includes a pressure side (94)...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	PRAISNER, Thomas J, NASH, Timothy Charles
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 component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil (78) extends from the radially outer side of the platform. The airfoil (78) includes a pressure side (94) that extends between a leading edge (82) and a trailing edge (84). A suction side (96) extends between the leading edge (82) and the trailing edge (84). A curvature inflection point (100) is located between 30% and 70% of an axial chord length (b x ) of the airfoil (78).