F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 5/10 (2006.01) B23P 15/04 (2006.01) F01D 5/16 (2006.01) F01D 5/20 (2006.01)
Patent
CA 2464249
An airfoil (42) for a gas turbine engine (10) 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.
Dickman Robert Bruce
Hetico Rolf
Wadia Aspi R.
Wood Peter
Yen Hsin-Yi
Company General Electric
Craig Wilson And Company
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