Apparatus to reduce the vibrations of gas turbine rotor blades

An airfoil (42) for a gas turbine engine includes a leading edge (48), a trailing edge (50), a tip (54), a first side wall (44) that extends in radial span between an airfoil root (52) and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall (46) connecte...

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Bibliographische Detailangaben
Hauptverfasser:	YEN, HSIN-YI, WADIA, ASPI R, HETICO, ROLF, DICKMAN, ROBERT BRUCE, WOOD, PETER
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION ENGINES ENGINE PLANTS IN GENERAL HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	An airfoil (42) for a gas turbine engine includes a leading edge (48), a trailing edge (50), a tip (54), a first side wall (44) that extends in radial span between an airfoil root (52) and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall (46) connected to the first side wall at the leading edge and the trailing edge, wherein the second side wall extends in radial span between the airfoil root and the tip, such that the second side wall defines a second side of the airfoil. The airfoil also includes a rib (70) that extends outwardly from at least one of the first side wall and the second side wall, such that a natural frequency of chordwise vibration of the airfoil is increased to a frequency that is not present within the gas turbine engine during engine operations.