FIELD: turbines or turbomachines.
SUBSTANCE: invention relates to movable blade (34) for a gas turbine engine comprising shank (41) configured to be inserted into receiving element (62) of rotor disc (38) for a gas turbine engine, shelf (48) carried by shank (41) , and blade blade (42) protruding from flange (48). Shelf (48) comprises upstream collar (50). According to invention, upstream collar (50) comprises tab (54) for engaging disc with locking cutout (64) so as to retain blade (34) in axial direction relative to disc (38), in accordance with longitudinal direction (XX) of receiving element (62).
EFFECT: easy installation and axial retention of the blade relative to the disk along the longitudinal direction, providing greater compactness of the blade, which reduces the weight of the blade and limits leakage.
9 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| IMPELLER FOR TURBOMASHINERY | 2012 |
|
RU2622351C2 |
| DAMPER FOR TURBINE ROTOR ASSEMBLY | 2013 |
|
RU2672201C2 |
| LOW-SPEED BALANCING METHOD OF COMPRESSOR ROTOR FOR GAS TURBINE PLANT | 2017 |
|
RU2711601C1 |
| METHOD OF TURBOMACHINE MANUFACTURE AND GRINDING MACHINE FOR ITS EMBODIMENT | 1996 |
|
RU2162782C2 |
| GAS TURBINE ENGINE DISTRIBUTOR, GAS TURBINE ENGINE TURBINE AND GAS TURBINE ENGINE | 2009 |
|
RU2506431C2 |
| GAS TURBINE ENGINE, FOR EXAMPLE AIRCRAFT TURBOJET ENGINE | 2005 |
|
RU2373402C2 |
| ENGINE WITH COMPOUND TURBINE COOLING | 2007 |
|
RU2447302C2 |
| STATOR VANE ASSEMBLY FOR LIGHTWEIGHT GAS TURBINE AND GAS TURBINE WITH SUCH ASSEMBLY | 2009 |
|
RU2515694C2 |
| TURBINE BLADE AND METHOD OF ASSEMBLY OF TURBINE ROTOR WITH SUCH BLADE | 2009 |
|
RU2517992C2 |
| ROTOR DISK OF GAS-TURBINE ENGINE (VERSIONS) | 2001 |
|
RU2281420C2 |
