ELASTIC-DAMPER SUPPORT OF TURBOJET ENGINE Russian patent published in 2014 - IPC F02C7/06 F16C27/00 

FIELD: engines and pumps.

SUBSTANCE: elastic-damper support of a turbojet engine includes an inner bushing connected with a C-shaped elastic element, a support ring and a rear flange of the labyrinth. The support ring is made as a whole with the rear flange of the labyrinth. Between the support ring and the inner bushing there is a perforated intermediate bushing. And between the perforated intermediate bushing and the inner bushing there is a damper cavity. Holes of the intermediate bushing are made as capable of communicating circular channels of oil supply in the support ring with a slot damper cavity. Radial ledges on the rear tail of the intermediate bushing are engaged with axial ledges of the rear tail of the inner bushing. On the radial rib of the perforated intermediate bushing there is an oil supply jet, which is L-shaped in the cross section. The radial tail of the jet is arranged between composite parts of the C-shaped elastic element.

EFFECT: increased reliability and efficiency of operation of an elastic-damper support, reduced weight of support design.

2 dwg