FIELD: machine building.
SUBSTANCE: invention relates to aircraft engine building, namely to design of rotors of axial turbines of turbojet engines (TJE). In the high-pressure turbine rotor of the turbojet engine, containing the main disk with cooled working blades installed on it and a cover disc attached to it by means of a bayonet connection, forming with the main disc cooling air supply channels to the tail part of the working blades, wherein in the rim of the main disc between the working blades there are radial slots, and the cover disc contains mating slots, in which the latches are installed, fixed in the radial direction, according to the present invention, retainers are made in the form of pins, and mating slots are formed between protrusions made along the circumference on the end surface of the covering disc.
EFFECT: improved reliability of the cover disc during operation of the turbojet engine and, as a consequence, improved reliability of the turbojet engine as a whole.
3 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ROTOR OF AXIAL GAS TURBINE | 2017 |
|
RU2647265C1 |
| TURBOCHARGER ROTOR | 2023 |
|
RU2810101C1 |
| ROTOR OF AXIAL GAS TURBINE | 2013 |
|
RU2530961C1 |
| AXIAL GAS TURBINE ROTOR | 2013 |
|
RU2529271C1 |
| TURBOJET TURBINE ROTOR | 2012 |
|
RU2493371C1 |
| TURBOJET LOW-PRESSURE COMPRESSOR LAST STAGE DISC | 2014 |
|
RU2565110C1 |
| IMPELLER WHEEL OF THIRD STAGE OF HIGH PRESSURE COMPRESSOR (HPC) ROTOR OF TURBOCHARGER ENGINE (VARIANTS), HPC ROTOR IMPELLER WHEEL DISC, HPC ROTOR IMPELLER WHEEL BLADE, HPC ROTOR IMPELLER WHEEL BLADE RING | 2016 |
|
RU2630921C1 |
| ROTOR FORTH 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 |
|
RU2630919C1 |
| COOLED HIGH-PRESSURE TURBINE | 2016 |
|
RU2623622C1 |
| TURBOJET LOW-PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2014 |
|
RU2565108C1 |
