FIELD: turbines or turbomachines.
SUBSTANCE: invention relates to blades of rotors of turbomachines. Turbomachine rotor blade comprises blade root and blade top spaced apart by blade height (h) together with at least one intermediate section (112a), representing negative tangential inclination to feather back, and far section (112b), located between intermediate section (112a) and blade tip and representing positive tangential inclination to airfoil trough, in which far section (112b) extends not more than 30 % of said height (h) of the blade.
EFFECT: invention allows improving aerodynamic and mechanical properties of blades of rotors of turbomachines.
13 cl, 18 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBOMACHINE ROTOR BLADE | 2013 |
|
RU2635734C2 |
| TURBOMACHINE BLADE, TURBOMACHINE COMPRESSOR, TURBOMACHINE TURBINE AND TURBOMACHINE | 2011 |
|
RU2603204C2 |
| GAS TURBINE ENGINE ROTOR BLADE | 2014 |
|
RU2707019C2 |
| BLADE OF TURBOMACHINE STATOR COMPRISING CONVEX SECTION | 2012 |
|
RU2641768C2 |
| GAS-TURBINE ENGINE VANE WITH PROFILE PROVIDING IMPROVED AERODYNAMIC AND MECHANICAL PROPERTIES | 2013 |
|
RU2624677C2 |
| TURBOMACHINE BLADE WITH ASYMMETRICAL COMPLEMENTARY CONFIGURATION | 2011 |
|
RU2553872C2 |
| ROTOR BLADE OF TURBOMACHINE AND TURBOMACHINE HAVING SAID BLADE | 2013 |
|
RU2587802C2 |
| TURBOJET LOW-PRESSURE COMPRESSOR ROTOR IMPELLER BLADE | 2014 |
|
RU2565135C1 |
| BLADE OF TURBOMACHINE, IN PARTICULAR FOR MADE AS A WHOLE MONOWHEEL | 2012 |
|
RU2607712C1 |
| BLADE AND DIHEDRAL ANGLE OF BLADE | 2014 |
|
RU2730192C2 |
