FIELD: mechanical engineering; turbojet engines.
SUBSTANCE: mixer of afterburner of turbojet engine relaters to members of afterburners making it possible to increase margin of vibratory combustion. Mixer 4 distributes air of outer loop and behind-the-turbine gas which pass through pockets 6 with lobes 5 and mix on section between end face edges 7 of mixer 4 and flame stabilizers 3. Fuel is delivered to gas through manifolds 2. Fuel-air mixture burn out behind flame stabilizers 3. Each portion of fuel from manifold 2 gets into air flow, each element of which has its momentum and direction. Thanks to it each portion of fuel from manifolds 2 has its own time for preparation to combustion and its own burnout time, so afterburner of double-flow turbojet engine has low tendency to vibratory combustion.
EFFECT: increased margin of vibratory combustion.
| Title | Year | Author | Number |
|---|---|---|---|
| AFTERBURNER MIXER OF BYPASS OF BYPASS TURBO-JET ENGINE | 1995 |
|
RU2117805C1 |
| MIXER FOR AFTERBURNER OF DOUBLE-CONTOUR TURBOJET ENGINE | 0 |
|
SU1813906A1 |
| AFTERBURNER COMBUSTION CHAMBER OF A DUAL-CIRCUIT TURBOJET ENGINE AND METHOD FOR ITS OPERATION | 2021 |
|
RU2784569C1 |
| TURBOJET ENGINE AFTERBURNER COMBUSTION CHAMBER COMBUSTION ZONE STABILIZATION METHOD AND THE TURBOJET ENGINE AFTERBURNER COMBUSTION CHAMBER | 2017 |
|
RU2680781C1 |
| AFTERBURNING CHAMBER OF DOUBLE-CIRCUIT TURBOJET ENGINE | 0 |
|
SU702758A1 |
| AFTERBURNER OF BYPASS GAS TURBINE MIXED-FLOW ENGINET (VERSIONS) | 2008 |
|
RU2366823C1 |
| BYPASS TURBOFAN ENGINE AFTERBURNER COMBUSTION CHAMBER | 2018 |
|
RU2682220C1 |
| DEVICE AND METHOD (VERSIONS) TO STABILISE FLAME IN TURBOJET ENGINE AFTERBURNER CHAMBER | 2009 |
|
RU2403422C1 |
| JET TURBINE ENGINE | 2011 |
|
RU2480604C1 |
| METHOD OF INCREASING A REACTIVE THRUST IN A TURBOREACTIVE TWO-CIRCUIT ENGINE AND A TURBOREACTIVE TWO-CONCURRENT ENGINE FOR ITS IMPLEMENTATION | 2017 |
|
RU2665760C1 |
