FIELD: engines and pumps.
SUBSTANCE: invention relates to gas turbines. Gas turbine support (1) comprises labyrinth seal (16) arranged between stator (2) and rotor (18). Oil feed jet (7) is arranged on the front side of bearing (6) comprising smooth outer ring (5) and inner ring (8). The latter has radial collars (11) and (12), as well as axial (9) and radial (10) oil feed channels. Bearing cage (13) is centered by collars (11) and (12) of inner ring (8). Rear side of bearing (6), between inner ring (8) and seal labyrinth (15), thrower ring (19) is arranged with its peripheral part (20) inclined towards the bearing. Diametre D, along bearing inner ring race, vs inner diametre d of jet flange radial collar, on the outer ring rear side, is 1.01 to 1.1.
EFFECT: efficient cooling of bearing to add to gas turbine support reliability.
2 dwg
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