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US 10,480,535 B2Granted
Fan rotor with flow induced resonance control
AssigneePratt & Whitney Canada Corp.
InventorsIgnatius Theratil, Krishna Balike
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AssigneePratt & Whitney Canada Corp.
InventorsIgnatius Theratil, Krishna Balike
Estimating the term…
A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor blades, the first set of rotor blades having a baseline profile and the second set of rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode. The cutback may be a leading edge cutback at a span position located a distance away from the hub between 20% and 50% of the total span length. The selected natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 5th natural vibration mode.
A fan for a gas turbine, the fan comprising fan blades circumferentially distributed around and extending a full span length from a central hub, the fan blades including alternating first fan blades and second fan blades, the first fan blades having a baseline profile and the second fan blades having a modified profile being the same as the baseline profile but for a leading edge cutback, the leading edge cutback extending from a first span position to a second span position, wherein the first span position is located at a distance away from the hub not exceeding 50% of the total span length and the second span position is located at a distance away from the hub exceeding 20% of the total span length, the first span position and the second span position are respectively located radially outwardly of and radially inwardly of a span location corresponding to a maximum deflection point for a selected natural vibration mode of the first fan blades, the selected natural vibration mode is a natural vibration mode higher than a 1st natural vibration mode.
A rotor for a gas turbine, the rotor comprising rotor blades circumferentially distributed around and extending a total span length from a central hub, the rotor blades including alternating first rotor blades and second rotor blades, the first rotor blades having a leading edge baseline profile and the second rotor blades having a leading edge profile with a leading edge cutback relative to the baseline profile, the leading edge cutback extending from a first span position to a second span position, wherein the first span position is located at a distance away from the hub not exceeding 50% of the total span length and the second span position is located at a distance away from the hub exceeding 20% of the total span length.
A rotor for a gas turbine, the rotor comprising rotor blades circumferentially distributed around and extending a total span length from a central hub, the rotor blades including alternating first rotor blades and second rotor blades, the first rotor blades having a baseline profile and the second rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode, wherein the cutback is located in a leading edge of the second rotor blades and extends from a from a first span position to a second span position, the first span position is located at a distance away from the central hub not exceeding 50% of the total span length and the second span position is located at a distance away from the central hub exceeding 20% of the total span length, and the selected natural vibration mode is a natural vibration mode higher than a 1st natural vibration mode.
Dependencies are inferred from the claim text.