LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE Russian patent published in 2017 - IPC F04D29/32 B01J3/00 

FIELD: engines and pumps.

SUBSTANCE: compressor pf low pressure (CPV) bypass two-shaft gas turbine engine (GTE) is made of aircraft-type axial, four-stage with the inlet guide vanes (IGV). Stator housing CPV blade rows equipped with guide vanes (ON) of the blade, respectively the first, second and third-stage and dual-straightener. CPV has front and rear bearing of the rotor shaft. Front support fixed in the housing CPV BHA. Back support - in the intermediate housing (PC) engine. The rotor shaft includes a reel-disk and cylindrical components, the first of which includes the impellers on the number of rotor stages. Bearings share the supports on the stator and rotor parts. The stator portion includes a front support bearing housing coupled with the bearing housing and the hub of the BHA to form a compact ring cavities. A cavity is provided with an elastic ring and the ring band is provided with perforations distributed in the form of holes. Another annular cavity contains the element elastic damping torsional vibration system with elastic cross members. The back support comprises a rotor shaft supporting ball bearings and an outer clamping member provided with an open collector for collecting and supplying pressurized coolant to the bearing and supplying fluid to the labyrinth ring with access to the oil chamber. The back support body is equipped with an additional row of holes for the flow of oil in the oil chamber. Reel-disk component CPV rotor shaft provided with radial and angular configuration of the outer surface of the rim disc impellers at all levels, combined with the inner surface of the engine running on an axial section flow together rims rotor shaft drives the flow of the working fluid. The blades of impellers are made with a spiral twist with respect to the axis of the pen, to create a variable adjustment angle of the pen γ_mouth installation profile stylus between the chord line and the front sections of the lattice in the plane sweep cylindrical section blade row.

EFFECT: invention allows to extend the operating range of the compressor stable damped oscillation of the rotor shaft without entering the resonant frequency, increase the efficiency of dynamic stability and service life without increasing the material consumption of the compressor and the engine as a whole.

24 cl, 10 dwg