FIELD: engine building.
SUBSTANCE: invention relates to the field of engine building and can be used to create jet thrust on aircraft and stationary power plants. The combined pulsating output device of a turbojet bypass gas turbine engine with separate outer and inner circuits contains a tapering sonic nozzle in the inner circuit, and a two-dimensional gas-dynamic resonator made in the form of a ring element with a a resonator cavity, the traction wall of which is made in the form of a torus dissected in cross section, while annular protrusions are formed on the outer and inner walls of the outer contour, forming an annular gap with the corresponding outer and inner edges of the resonator cavity of the two-dimensional gas-dynamic resonator.
EFFECT: invention provides an increase in thrust while maintaining the weight and dimensions of the turbofan engine.
1 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| COMBINED PULSATING DETONATION OUTPUT DEVICE OF A TURBOJET BYPASS GAS TURBINE ENGINE | 2022 |
|
RU2799996C1 |
| COMBINED PULSATING DETONATION OUTPUT DEVICE OF TURBOJET BYPASS GAS TURBINE ENGINE WITH FUEL SUPPLY TO EXTERNAL CIRCUIT | 2023 |
|
RU2823402C1 |
| METHOD OF OPERATING TURBOFAN AIRCRAFT ENGINES WITH EXTERNAL FAN MODULE | 2014 |
|
RU2580608C2 |
| SOUND-ABSORBING DEVICE IN TWO-CIRCUIT TURBOJET ENGINE | 2002 |
|
RU2230208C2 |
| AIRCRAFT POWER PLANT | 2016 |
|
RU2644721C2 |
| METHOD OF INCREASING THRUST OF DUAL-FLOW TURBOJET ENGINE | 2015 |
|
RU2622345C2 |
| BYPASS TURBOJET ENGINE | 2017 |
|
RU2661427C1 |
| TURBOJET ENGINE | 2004 |
|
RU2277181C2 |
| MIXER OF BYPASS TURBOJET ENGINE | 2004 |
|
RU2265130C1 |
| METHOD OF INCREASING A REACTIVE THRUST IN A TURBOREACTIVE TWO-CIRCUIT ENGINE AND A TURBOREACTIVE TWO-CONCURRENT ENGINE FOR ITS IMPLEMENTATION | 2017 |
|
RU2665760C1 |
