FIELD: engines and pumps.
SUBSTANCE: combustion chamber houses two or three rows of nozzles. Stoichiometric fuel combustion occurs in the first and/or extra row of said nozzles. "Atmofuel" is forced to the second row of nozzles in the amount sufficient for cooling of gas downstream of the first row to the level acceptable for turbine. Thereafter, evaporated fuel is burnt in afterburner chamber in the mix with air of the engine second stage. Extra amount of fuel is injected into "atmofuel" nozzles and/or afterburner chamber nozzles to be combusted completely in the mix with the turbine second stage air.
EFFECT: higher thrust, expanded adjustment range.
3 cl
Title | Year | Author | Number |
---|---|---|---|
METHOD OF TURBOJET AFTERBURNING AND ENGINE TO THIS END (VERSIONS) | 2011 |
|
RU2474718C2 |
METHOD OF GAS TURBINE ENGINE AFTERBURNING | 2013 |
|
RU2523510C1 |
THREE-ZONE ENGINE (VERSIONS) | 2008 |
|
RU2419035C2 |
HYPERSONIC ENGINE (VERSIONS) | 2012 |
|
RU2529601C9 |
STAROVEROV HIGH-ENERGY ENGINE (VERSIONS) | 2008 |
|
RU2391529C2 |
STAROVEROV'S SPACECRAFT (VERSIONS) AND/OR ALGORITHMS OF ITS OPERATION | 2012 |
|
RU2503592C1 |
METHOD OF AIRCRAFT ENGINE AUGMENTATION | 2014 |
|
RU2573438C1 |
METHOD FOR FORCING TURBOJET BYPASS ENGINE | 2023 |
|
RU2838007C2 |
AFTERBURNER OF BYPASS GAS TURBINE MIXED-FLOW ENGINET (VERSIONS) | 2008 |
|
RU2366823C1 |
TURBOJET ENGINE | 2019 |
|
RU2727532C1 |
Authors
Dates
2015-11-10—Published
2014-01-17—Filed