TURBOJET ENGINE ROTOR SHAFT SUPPORT (VERSIONS), TURBOJET ENGINE ROTOR SHAFT SUPPORT GARTER SEAL, TURBOJET ENGINE ROTOR SHAFT SUPPORT SEALING GARTER ASSEMBLY, TURBOJET ENGINE ROTOR SHAFT SUPPORT GARTER SEAL RING SECTION Russian patent published in 2016 - IPC F16F15/02 B01J3/00 

FIELD: engines and pumps.

SUBSTANCE: invention relates to engine building. TJE LPC rotor shaft support is equipped with rotor shaft oscillations elastic-hydraulic damping system and comprises roller bearing. Stator part comprises roller bearing body, connected to support body. Support body is enveloped with LPC VGV body with formation of two annular cavities. One of said cavities is equipped with resilient ring, which is equipped with single-sided projections from outer and inner sides, mutually shifted in circle in one with angular frequency of γ_v.u.k.=(2.2÷4.8) [units/rad]. Second cavity comprises of "squirrel cage" type element made in support body in form of longitudinal resilient beams system, separated by slits made with width, in (1.1÷2.4) times higher than beams width, and located with angular frequency γ_b.b.k., defined in range γ_b.b.k.=(7.2÷14.4) [units/rad]. support stator part comprises two circular elements equipped with labyrinths covers, and two mating crested labyrinth rings. Support rotor part comprises trunnion with roller bearing inner race installed at trunnion front end. On adjacent to it section garter seal contact bushing is installed resting in first labyrinth crested ring. First labyrinth crested ring together with labyrinth mating cover divides breathing cavity with air supercharging cavity, which volume is limited by second labyrinth crested ring, installed on trunnion conical diaphragm, forming integral unit with cylindrical section and permanently connected with rotor shaft first stage disk. Inside trunnion end bushing is inserted. Garter seal includes contact bushing with movable abuting to garter sealing rings contact surfaces. Garter consists of three multi-section rings. Its inner sealing and radially embracing outer rings are installed in garter on front side. Third ring is made rear and adjoins first two with side edge. Each of garter rings is made of local sections assembled with angular frequency of γ_s.b.u.=(0.47÷0.79) [unit/rad]. Garter rings are equipped with discharge air channels. Garter external and rear rings outer surfaces are equipped with annular slot for spring rings tightening section. From axial displacement garter is elastically fixed by thrust and retaining rings. In each rear ring section at least two blind holes are made, in which compression springs are installed resting against stop ring.

EFFECT: group of inventions technical result consists in engine stable operation operating modes range expansion with rotor shaft vibrations damping without entering into resonance frequencies and increase of compressor and engine as a whole service life.

16 cl, 5 dwg