FAN OF GAS TURBINE ENGINE Russian patent published in 2015 - IPC F02C7/06 F01D25/18 F01D25/16 

FIELD: engines and pumps.

SUBSTANCE: fan (1) of a gas turbine engine includes a radial thrust bearing (9), an inner ring (14) of which is fixed with a nut (10) with radial ledges (22) as turnkey on a threaded tail (13) and a jet (26) of oil supply for lubrication. The nut (10) is made with a conical tail (16) directed to a fan axis (15). On the outer surface (17) of the tail (16) there is an inductor (18) of a rotation frequency sensor (20) installed in the form of radial ledges. On the inner surface (23) of the conical tail (16) there is a radial circular rib (24) with formation of a circular cavity (25) of oil supply. The cavity of oil supply at the inlet is connected with the jet (26), and at the outlet - with radial channels (30) in the inner ring (14) of the bearing. The ratio of the inner diameter D of the inner ring of the radial-thrust bearing of the fan to the axial distance L between radial ledges of the inductor and radial ledges of the threaded tail of the nut is within 3…6. The ratio of the inner diameter D to the inner diameter d of the radial circular ribs on the conical tail of the nut is within 1.05…1.2.

EFFECT: by means of even oil supply from the side of an inner ring of a bearing, and also by means of exclusion of false signals on an inductive sensor, reliability of a gas turbine engine fan increases.

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