Damper for a turbine rotor assembly

A damper (36) for a turbine rotor assembly (22) of a gas turbine engine (100) may include a forward plate (76) with a forward face (45) and an aft face (75), and an aft plate (78) with a forward face (88) and an aft face (87). The aft face of the forward plate may be connected to the forward face of...

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Bibliographische Detailangaben
Hauptverfasser:	FAULDER LESLIE JOHN, TARCZY JEFFREY EUGENE
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 damper (36) for a turbine rotor assembly (22) of a gas turbine engine (100) may include a forward plate (76) with a forward face (45) and an aft face (75), and an aft plate (78) with a forward face (88) and an aft face (87). The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal structure (80). An area of the aft plate in a plane transverse to the longitudinal structure may be greater than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a pocket (71) on the forward face of the forward plate.