FIELD: engines and pumps.
SUBSTANCE: claimed disc is composed of monoelement including the ring changing into circular web reinforced with hub which has the central bore. Said ring is asymmetrically connected with disc web to make different-arm circular conical inclined flanges. Rear flange can be fixed with the spacer facing the disc of the next stage. For permanent joint with the disc of the next stage bores for fasteners are made via said spacer in disc web. Disc ring is provided with the system of grooves for securing of blades. Lengthwise axis of every groove makes with rotor shaft axis in projection on arbitrary axial plane perpendicular to the blade root radial axis the pitch angle α of the blade butt. Grooves are uniformly spaced apart in disc perimeter at claimed angular frequency and provided with side faces in cross-section to make the element of lock joint with the blade butt. Said web is provided with conical circular element that features the angle of generatrix inclination to the disc geometrical axis.
EFFECT: higher efficiency and longer life under all operating conditions of the compressor third stage impeller without increase in disc material input.
5 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR THIRD STAGE DISC (VERSIONS) | 2015 |
|
RU2603222C1 |
| ROTOR SHAFT OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE | 2014 |
|
RU2565113C1 |
| ROTOR SHAFT OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE, CONNECTION ASSEMBLY OF ROTOR SHAFT DISKS OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE | 2014 |
|
RU2565090C1 |
| TURBOJET LOW-PRESSURE COMPRESSOR SECOND STAGE DISC | 2014 |
|
RU2565139C1 |
| ROTOR SHAFT OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE, CONNECTION ASSEMBLY OF ROTOR SHAFT DISKS OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE, SPACER OF CONNECTION ASSEMBLY OF ROTOR SHAFT DISKS OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE | 2014 |
|
RU2565133C1 |
| GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR SECOND STAGE DISC (VERSIONS) | 2015 |
|
RU2603218C1 |
| ROTOR SHAFT OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE, CONNECTION ASSEMBLY OF ROTOR SHAFT DISKS OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE, SPACER OF CONNECTION ASSEMBLY OF ROTOR SHAFT DISKS OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE | 2014 |
|
RU2565141C1 |
| TURBOJET ENGINE LOW-PRESSURE COMPRESSOR ROTOR SHAFT (VERSIONS) | 2014 |
|
RU2573417C2 |
| TURBOJET LOW-PRESSURE COMPRESSOR ROTOR SHAFT SECTION (VERSIONS) | 2014 |
|
RU2573408C2 |
| SECOND STAGE DISC OF TURBOJET ENGINE LOW-PRESSURE COMPRESSOR ROTOR SHAFT (VERSIONS) | 2015 |
|
RU2603215C1 |
