Damper assemblies for rotating drum rotors of gas turbine engines

A gas turbine engine includes a rotatable drum rotor having a plurality of blades secured thereto. The blades extend radially inward of the rotatable drum rotor. The gas turbine engine also includes a support frame mounted radially outward of the rotating drum rotor and a rotor support system having...

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Bibliographische Detailangaben
Hauptverfasser:	Pankaj, Peeyush, Payyoor, Narayanan, Puranik, Shashank Suresh
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS 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 gas turbine engine includes a rotatable drum rotor having a plurality of blades secured thereto. The blades extend radially inward of the rotatable drum rotor. The gas turbine engine also includes a support frame mounted radially outward of the rotating drum rotor and a rotor support system having a bearing assembly positioned between the rotatable drum rotor and the support frame. The bearing assembly includes, at least, a stationary component and at least one rotatable component. Further, the gas turbine engine includes a damper assembly for securing between the support frame and the rotatable drum rotor. Moreover, the damper assembly includes at least one damper secured between the support frame and the stationary component of the bearing assembly or to a surface of the rotatable drum rotor. As such, the damper(s) is configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.