FIELD: aviation.
SUBSTANCE: invention relates to the field of aero-acoustic control of fixed blades in a turbomachine of an aircraft or in a test bench for such a turbomachine. The turbomachine with a fan located at the front has annular wall (160) containing slat (16) designed for flow separation into a primary flow and a secondary flow, and having a front edge, input guiding blades designed for guiding the primary flow, and output guiding blades designed for guiding the secondary flow. The front edge of slat (16) has gear profile (28) containing a sequence of gears and recesses.
EFFECT: invention provides for reduction in noise conditioned by interaction between a vortex wake of a fan blade and a slat.
7 cl, 13 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| PROFILED AERODYNAMIC STRUCTURE AND TURBOMACHINE FOR AIRCRAFT (OPTIONS) | 2019 |
|
RU2782555C2 |
| PROFILED STRUCTURE FOR AIRCRAFT OR GAS-TURBINE ENGINE | 2019 |
|
RU2789369C2 |
| RADIAL IMPELLER AND IMPELLER BLADES | 2006 |
|
RU2310774C1 |
| RADIAL IMPELLER AND AIR DUCT FAN WITH THE SAID IMPELLER | 2007 |
|
RU2330189C1 |
| FAN UNIT WITH FREE RADIAL WHEEL ROTOR | 2007 |
|
RU2429386C2 |
| CENTRIFUGAL FAN (VERSIONS) | 2007 |
|
RU2330188C1 |
| RADIAL BLOWER | 2011 |
|
RU2470193C1 |
| RADIAL WHEEL ROTOR | 2010 |
|
RU2429385C1 |
| CENTRIFUGAL FAN | 0 |
|
SU1726850A1 |
| TURBULENCE SENSOR OF TURBOMACHINE COMPRESSOR | 2018 |
|
RU2757091C2 |
