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US 6,042,338 AGranted
Detuned fan blade apparatus and method
AssigneeAlliedSignal Inc.
InventorsPerry W. Brafford, Yoseph Gebre-Giorgis, Durbha V. Murthy
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AssigneeAlliedSignal Inc.
InventorsPerry W. Brafford, Yoseph Gebre-Giorgis, Durbha V. Murthy
Estimating the term…
A propulsion engine fan incorporates two sets of blades with recessed portions formed along the surface of each blade. One set of blades has a higher resonant frequency than the other set of blades. In an illustrative embodiment of the invention, first and second blade groups each comprise an airfoil portion forming a surface for directing the flow of a working fluid through the engine. Each of the first group of blades has first and second recessed regions formed from the blade surface and has a first resonant frequency. Each of the second group of blades has third and fourth recessed regions formed from the blade surface and has a second resonant frequency less than the first resonant frequency. The first and second group blades are arranged in an alternating pattern along the rotor portion of the fan.
In a gas turbine engine having a rotating component with a plurality of blades extending therefrom, said component comprising:
A method of preventing flutter and reducing resonant response associated with propulsion engine blades, said blades being disposed along a rotor, each of said blades having a surface for directing the flow of a working fluid through the engine, the method comprising the steps of:
Dependencies are inferred from the claim text.