SUPPORTING ELONGATED ROTATING ASSEMBLY WITHIN A TURBINE ENGINE

A turbine engine (20) is provided that includes a first rotating assembly (80), a bearing (90D), a turbine engine core (34) and a flowpath (52). The first rotating assembly (80) includes a propulsor rotor (66), a power turbine rotor (67) and a power turbine shaft (78) coupled with and axially betwee...

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Bibliographische Detailangaben
Hauptverfasser:	SOBANSKI, Jon E, SNYDER, Jacob C
Format:	Patent
Sprache:	eng ; fre ; ger
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 turbine engine (20) is provided that includes a first rotating assembly (80), a bearing (90D), a turbine engine core (34) and a flowpath (52). The first rotating assembly (80) includes a propulsor rotor (66), a power turbine rotor (67) and a power turbine shaft (78) coupled with and axially between the propulsor rotor (66) and the power turbine rotor (67). The bearing (90D) rotatably supports the first rotating assembly (80) at an intermediate location (102) along the power turbine shaft (78). The turbine engine core (34) includes a second rotating assembly (84, 88) and a combustor (122). The second rotating assembly (84, 88) includes a core compressor rotor (68, 69) and a core turbine rotor (70, 71). The power turbine rotor (67) is arranged axially between the propulsor rotor (66) and the second rotating assembly (84, 88). The flowpath (52) extends sequentially across the core compressor rotor (68, 69), the combustor (122), the core turbine rotor (70, 71) and the power turbine rotor (67) from an inlet (54) into the flowpath (52) to an exhaust (56) from the flowpath (52).