FIELD: aircraft engineering.
SUBSTANCE: invention relates to device aimed at reduction of noise of gas-turbine engines. Proposed mixer of bypass turbojet engine contains nozzle, shroud and channels to pass gas and air of inner and outer loops located after shroud. Output edges of shroud are made in form of herringbones. Channels are formed by herringbones and two rows of alternating partitions, some of which being flat arranged in planes passing through axis of engine, and others are bent. Output edges of bent partitions lie in plane of flat partitions lower than flat partitions in direction of gas flow. Channel to pass air of outer loop is formed by herringbones, partitions and inner surface of nozzle. Channel to pass gas is formed by herringbones and partitions. Invention provides reduction of noise of bypass turbojet engine owing to multiple reflection of sound waves from mixer members and inner surface of nozzle and intensification of mixing of flows of inner and outer loops of engine.
EFFECT: reduced noises.
2 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ADJUSTABLE NOISE REDUCTION NOZZLE OF SUPERSONIC PASSENGER AIRCRAFT | 2023 |
|
RU2810871C1 |
| METHOD OF OPERATING TURBOFAN AIRCRAFT ENGINES WITH EXTERNAL FAN MODULE | 2014 |
|
RU2580608C2 |
| NOISE-SUPPRESSING NOZZLE OF AIR-JET ENGINE | 2019 |
|
RU2732360C1 |
| ADJUSTABLE MIXER FOR CHANGING BY-PASS RATIO OF BY-PASS TURBOJET ENGINE | 2003 |
|
RU2249120C9 |
| BYPASS TURBOJET ENGINE WITH AIRFLOW REDISTRIBUTION AT INLET | 2010 |
|
RU2447308C2 |
| OUTPUT DEVICE OF A TURBOJET ENGINE | 2023 |
|
RU2807307C1 |
| DOUBLE-FLOW TURBOJET ENGINE NOZZLES SYSTEM | 2018 |
|
RU2716651C2 |
| AIRCRAFT POWER PLANT | 2016 |
|
RU2644721C2 |
| BYPASS TURBOJET ENGINE | 2017 |
|
RU2661427C1 |
| METHOD OF INCREASING A REACTIVE THRUST IN A TURBOREACTIVE TWO-CIRCUIT ENGINE AND A TURBOREACTIVE TWO-CONCURRENT ENGINE FOR ITS IMPLEMENTATION | 2017 |
|
RU2665760C1 |
