FIELD: manufacture of engines. SUBSTANCE: jet engine is provided with air turbine, second loop and straightener fitted before compressor. Power and air turbines are provided with special mechanism for shifting from one mode to another. Passage feeding the compressed air to additional combustion chamber is circular in shape and is provided with air preheaters, circular slot for connection with main combustion chamber and closing ring. Additional combustion chamber is mounted in after-turbine space whose wall is formed by combustion chamber and terminates in cooled fairing with exhaust branch pipe, mixer is located after additional combustion chamber. EFFECT: higher efficiency. 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBOJET ENGINE | 1994 |
|
RU2109974C1 |
| STEAM-GAS PLANT | 1994 |
|
RU2090762C1 |
| TURBOJET ENGINE WITH CONTROLLABLE BY-PASS RATIO | 2002 |
|
RU2204045C1 |
| TURBOJET ENGINE | 2019 |
|
RU2727532C1 |
| AIRCRAFT CONROD-FREE FAN ENGINE | 2010 |
|
RU2433292C1 |
| METHOD OF CREATING A TRAIL AND POWER INSTALLATION FOR ITS IMPLEMENTATION | 2017 |
|
RU2680214C1 |
| TURBOJET ENGINE AFTERBURNER COMBUSTION CHAMBER COMBUSTION ZONE STABILIZATION METHOD AND THE TURBOJET ENGINE AFTERBURNER COMBUSTION CHAMBER | 2017 |
|
RU2680781C1 |
| AIRCRAFT WITH GAS TURBINE ENGINE PROVIDED WITH TURBULENCE EJECTION PROPULSORS | 2013 |
|
RU2567914C2 |
| COOLING SYSTEM FOR TURBINE ELEMENTS OF TURBOJET | 2018 |
|
RU2706524C1 |
| METHOD OF INCREASING A REACTIVE THRUST IN A TURBOREACTIVE TWO-CIRCUIT ENGINE AND A TURBOREACTIVE TWO-CONCURRENT ENGINE FOR ITS IMPLEMENTATION | 2017 |
|
RU2665760C1 |
