FIELD: engines and pumps.
SUBSTANCE: fan blade (4) for an aircraft turbojet engine comprising a feather (6) axially extending between a leading edge (18) and a trailing edge (20) and comprising a plurality of sections of the feather arranged radially between the leg section (Spied) and the cross-section of the vortex (
). All feather cross-sections enclosed between the leg section (Spied) and the feather section (S30) are located at radial height which is 30% of the total radial height of the feather, and have a skeletal curve with an inflection point. The skeletal curve of the feather section is formed by the variations of the skeletal angle depending on the position along the blade chord, the skeletal angle is the angle formed between the tangent to each point of the blade skeleton and the axis of the engine.
EFFECT: reduction of the first bending mode without increasing weight and length of the turbojet engine.
7 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBOMACHINE BLADE, TURBOMACHINE COMPRESSOR, TURBOMACHINE TURBINE AND TURBOMACHINE | 2011 |
|
RU2603204C2 |
| TURBOMACHINE COMPONENT OR COLLECTION OF COMPONENTS AND ASSOCIATED TURBOMACHINE | 2014 |
|
RU2666933C1 |
| RECTIFIER OF GAS-TURBINE ENGINE WITH VANES OF IMPROVED PROFILE | 2013 |
|
RU2632350C2 |
| GAS TURBINE ENGINE BLADE WITH MAXIMUM THICKNESS RULE WITH HIGH FLUTTER STRENGTH | 2019 |
|
RU2794951C2 |
| IMPELLER OF AXIAL-FLOW FAN OR COMPRESSOR | 2001 |
|
RU2188340C1 |
| AXIAL BLOWER OR COMPRESSOR HIGH-RPM IMPELLER | 2007 |
|
RU2354854C1 |
| GAS TURBINE ENGINE BLADE MADE ACCORDING TO THE RULE OF DEFLECTION OF THE BLADE PROFILE WITH A LARGE FLUTTER MARGIN | 2019 |
|
RU2792505C2 |
| GAS-TURBINE ENGINE VANE WITH PROFILE PROVIDING IMPROVED AERODYNAMIC AND MECHANICAL PROPERTIES | 2013 |
|
RU2624677C2 |
| RADIAL COMPRESSOR | 2015 |
|
RU2674844C2 |
| BLADE OF COMPOSITE MATERIAL, COMPRESSOR OF GAS TURBINE ENGINE COMPRISING SUCH BLADE AND TURBOJET ENGINE | 2008 |
|
RU2498083C2 |
