FIELD: machine building.
SUBSTANCE: fan blade of a jet turbine engine with a double flow, which contains internal aerodynamic part (11) and external aerodynamic part (12), which are combined in radial direction (Z) and separated with platform (10). Internal aerodynamic part (11) includes one aerodynamic profile (13), and external aerodynamic part (12) includes at least two aerodynamic profiles (14); at that, leading edges of the above aerodynamic profiles (14) of the above aerodynamic part (12) of the blade are axially aligned in a row.
EFFECT: reduction of the number of fan blades at maintaining satisfactory quality owing to maintaining an increased relative pitch of the internal aerodynamic part of the fan blade.
8 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| FAN WITH VARIABLE ANGLE OF INSTALLATION BY VARIOUS ROTATION OF FAN DISCS | 2013 |
|
RU2644001C2 |
| LASH OF THE TURBOJET MOTOR FAN, TURBOJET ENGINE FAN AND TURBOJET ENGINE | 2013 |
|
RU2626886C2 |
| UNIT OF FAN ON BLADE, AND ALSO TURBOFAN GAS TURBINE ENGINE | 2007 |
|
RU2433290C2 |
| TURBOJET COMPRESSOR | 2009 |
|
RU2476678C2 |
| FAN BLADE | 2001 |
|
RU2272180C2 |
| BLADE PLATFORM AND FAN DISC FOR AIRCRAFT TURBINE ENGINE | 2017 |
|
RU2728547C2 |
| TOOL FOR UNSCREWING COUPLING NUT OF GAS TURBINE ENGINE MODULAR ROTOR | 2013 |
|
RU2645874C2 |
| DISC WITH FAN BLADES FOR TURBOMACHINE, TURBOMACHINE FAN AND AIRCRAFT ENGINE | 2016 |
|
RU2716953C2 |
| FAN, IN PARTICULAR, FOR TURBINE ENGINE | 2014 |
|
RU2677769C1 |
| AXIAL FAN | 2004 |
|
RU2293883C2 |
