GAS TURBINE ENGINE BLADE

A component (64) for a gas turbine engine (20) includes a platform (76) that has a radially inner side and a radially outer side. A root portion (74) extends from the radially inner side of the platform (76). An airfoil (78) extends from the radially outer side of the platform (76). The airfoil (78)...

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Bibliographische Detailangaben
Hauptverfasser:	BALZER, Wolfgang, 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 (64) for a gas turbine engine (20) includes a platform (76) that has a radially inner side and a radially outer side. A root portion (74) extends from the radially inner side of the platform (76). An airfoil (78) extends from the radially outer side of the platform (76). 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 ratio of maximum thickness (T max ) to axial chord length (b x ) is between 0.40 (T max /b x ) and 0.65 (T max /b x ).