FIELD: machine building.
SUBSTANCE: blade installed on the disc includes blade root and blade shank. Blade shank includes the first, the second and the third teeth and the first, the second and the third necks. Each tooth includes contact surface and non-contact surface. Angle between non-contact surface of the first tooth and contact surface of the second tooth and between non-contact surface of the second tooth and contact surface of the third tooth is optimised for reduction of local and average stresses and is symmetrical relative to the axis perpendicular to central line of blade shank. As per the other version of the blade, the above angle is approximately 70.6°. One more invention of the group refers to the turbine containing the blade and rotor disk. Rotor contact surfaces are located relative to non-contact surfaces of rotor at the angle that is equal to the angle of contact surfaces of blade and non-contact surface of blade; at that, angle is optimised to reduce local and average stresses between contact surfaces and is essentially symmetric relative to the axis perpendicular to central line of blade shank.
EFFECT: inventions allow decreasing local loads on rotor without increasing average values of stresses.
16 cl, 8 dwg
Title | Year | Author | Number |
---|---|---|---|
STEAM-TURBINE ENGINE LOW-PRESSURE STAGE WORKING BLADE | 2009 |
|
RU2515582C2 |
DOVETAIL JOINT OF TURBINE ROTOR BLADE AND WHEEL | 2002 |
|
RU2303703C2 |
ROTOR BLADE (VERSIONS), ROTOR AND ROTOR DISK OF GAS-TURBINE ENGINE | 2000 |
|
RU2228445C2 |
ROTOR BLADE FOR GAS-TURBINE ENGINE (VARIANTS) | 2013 |
|
RU2626871C2 |
TURBINE BLADE SECURING FOR TURBINE MACHINE | 2010 |
|
RU2562687C2 |
ROTATING BLADE OF STEAM TURBINE (VERSIONS) | 2008 |
|
RU2472943C2 |
IMPROVED ATTACHMENT OF BLADES ON DISK OF GAS-TURBINE ROTOR | 2002 |
|
RU2302532C2 |
THIRD STAGE DISC OF TURBOJET ENGINE LOW-PRESSURE COMPRESSOR ROTOR SHAFT (VERSIONS) | 2015 |
|
RU2603219C1 |
OPEN AIR PROPELLER FOR TURBINE MACHINE | 2011 |
|
RU2558411C2 |
TURBOJET ENGINE LOW-PRESSURE COMPRESSOR SECOND STAGE ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603383C1 |
Authors
Dates
2013-01-10—Published
2008-07-15—Filed