FIELD: machine building.
SUBSTANCE: impeller of rotor of gas turbine engine has blades secured on the rotor disk using the ring locks "dovetail", O-rings, and seal plate, and has compensation hole on the disk rim. The seal plate is located on the internal surface of the blade flange, repeats its shape, and is made with possibility of gaps coverage between the blades. The compensation hole made in the disk rim connects the lock cavity with the internal cavity of the rotor with pressure reduced in comparison with the pressure in through part.
EFFECT: invention reduces weight and overall dimensions of the rotor elements.
3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR SECOND STAGE DISC (VERSIONS) | 2015 |
|
RU2603218C1 |
| GAS TURBINE ENGINE LOW PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603380C1 |
| GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR LAST STAGE DISC | 2015 |
|
RU2603220C1 |
| COMPRESSOR OF GAS-TURBINE ENGINE | 2002 |
|
RU2225538C2 |
| GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2611497C1 |
| GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR THIRD STAGE DISC (VERSIONS) | 2015 |
|
RU2603222C1 |
| TURBOJET LOW-PRESSURE COMPRESSOR LAST STAGE DISC | 2014 |
|
RU2565110C1 |
| GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR FIRST STAGE DISC (VERSIONS) | 2015 |
|
RU2603304C1 |
| GAS TURBINE ENGINE LOW PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603379C1 |
| TURBOJET LOW-PRESSURE COMPRESSOR THIRD STAGE DISC | 2014 |
|
RU2565140C1 |
