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. The elastic ring is provided with projections mutually offset circumferentially with the inside and outside of the ring in one angular frequency γ v.u.k.= (2.55÷3.82) [U/rad]. The tape is perforated ring in the form of dispersed holes. Another annular cavity contains the element elastic damping torsional vibration system with elastic cross members arranged at the frequency found in the invention. The rear rotor shaft support comprises a support-thrust bearing and an external coupling element. 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 γmouth 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.
22 cl, 8 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614708C1 |
| TURBOJET ENGINE LOW-PRESSURE COMPRESSOR THIRD STAGE ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603384C1 |
| TURBOJET LOW-PRESSURE COMPRESSOR ROTOR FOURTH-STAGE IMPELLER | 2015 |
|
RU2612282C1 |
| IMPELLER WHEEL OF SEVENTH STAGE OF HIGH PRESSURE COMPRESSOR (HPC) ROTOR OF TURBOCHARGER ENGINE (VERSIONS), HPC ROTOR IMPELLER WHEEL DISC, HPC ROTOR IMPELLER WHEEL BLADE, HPC ROTOR IMPELLER WHEEL BLADE RING | 2016 |
|
RU2630923C1 |
| GAS TURBINE ENGINE LOW PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603377C1 |
| TURBOJET ENGINE LOW-PRESSURE COMPRESSOR FIRST STAGE ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603382C1 |
| ROTOR EIGHTH STAGE IMPELLER OF HIGH-PRESSURE COMPRESSOR (HPC) OF TURBOJET ENGINE (VERSIONS), HPC ROTOR IMPELLER DISC, HPC ROTOR IMPELLER BLADE, HPC ROTOR IMPELLER BLADE RING | 2016 |
|
RU2630924C1 |
| ROTOR IMPELLER OF LP COMPRESSOR OF JET TURBINE ENGINE (VERSIONS) | 2014 |
|
RU2565091C1 |
| GAS TURBINE ENGINE LOW PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603379C1 |
| ROTOR SIXTH STAGE IMPELLER OF HIGH-PRESSURE COMPRESSOR (HPC) OF TURBOJET ENGINE (VERSIONS), HPC ROTOR IMPELLER DISC, HPC ROTOR IMPELLER BLADE, HPC ROTOR IMPELLER BLADE RING | 2016 |
|
RU2630922C1 |
