GAS TURBINE ENGINE Russian patent published in 2015 - IPC F02C3/04 F02C7/06 

FIELD: engines and pumps.

SUBSTANCE: on one end of the shaft rigidly connected with the turbine impeller, a cylindrical sleeve of the rotor is placed, and the rotor is designed with a possibility of its gas dynamical support, and on the free end the centrifugal compressor wheel is fixed which is fitted with a thrust bearing. On the cylindrical sleeve from the side, adjoining to the turbine wheel, the first bowl-shaped pivor journal of the first angular contact magnetic bearing with the bottom facing towards the turbine wheel is placed. On the free end of the shaft, thrusting each other, the bowl-shaped pivot journal of the second angular contact magnetic bearing with its bottom facing towards to the compressor wheel, the first and second thrust spade gas bearings are installed in series. Each radial magnetic bearing is implemented according to Halbach design, where it comprises a thin-walled cylindrical sleeve made from non-magnetic material, rods with trapezoidal cross-section made from magnetic material, permanent magnets designed as rods with trapezoidal cross-section. The thrust magnetic bearing has a footstep bearing made from a non-magnetic material, placed in a ring body, between the bottom of which and end surface of the pivot journal the sectors of permanent magnets are fixed. The radial and thrust magnetic bearings placed from the side of the turbine, are implemented using the magnetic material with a Curie point 900°C minimum.

EFFECT: invention ensures high bearing capacity of radial and thrust bearing units in operating mode with decrease of friction-related losses, reliable start at low temperatures, improvement of its operational reliability at high dynamical loads, increase of rotor stability to half-speed vortex, increase of mechanical efficiency.

2 cl, 4 dwg