FIELD: aircraft engineering.
SUBSTANCE: proposed nacelle comprises wall concentrically surrounding, at least, partially, the engine to make therewith a gas flow inner annular channel. Annular channel outlet end has nacelle walls confining outlet air flow area. Besides nacelle comprises means to displace nacelle wall part in lengthwise axis to vary said air flow area. Said lengthwise displacement creates in nacelle wall, at least, one opening with lengthwise size via which portion of inner flow, a leak flow, escapes radially while another part of inner flow directed by nacelle wall facilitates engine thrust. Nacelle incorporates the device for creating gas barrier extending along, at least, part of aforesaid opening. Gas barrier resists natural escape of said leak flow via said one opening.
EFFECT: increased thrust.
14 cl, 11 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| NACELLE OF AIRBORNE VEHICLE ENGINE, AND AIRBORNE VEHICLE CONTAINING SUCH NACELLE | 2007 |
|
RU2462608C2 |
| TAIL CONE FOR ROTARY GAS TURBINE ENGINE WITH MICRO-JETS | 2012 |
|
RU2605869C2 |
| BYPASS TURBOMACHINE WITH INDIRECT GAS EXHAUST THROAT CROSS-SECTION VARIATION AND METHOD OF SAID VARIATION | 2007 |
|
RU2446303C2 |
| ANTENNA SETTING UP AND TAKING UP WINCH DRIVE AIR TURBINE | 2004 |
|
RU2276272C2 |
| BYPASS TURBOMACHINE WITH REDUCED JET NOISE | 2008 |
|
RU2468232C2 |
| COOLING DEVICE FOR TURBOMACHINE PROVIDED WITH UNLOADING CIRCUIT | 2015 |
|
RU2753738C2 |
| METHOD AND SYSTEM OF AERO/HYDRODYNAMIC CONTROL OF NEWTONIAN FLUID FLOW IN RADIAL TURBOMACHINE | 2013 |
|
RU2642203C2 |
| TURBOJET ENGINE | 1992 |
|
RU2101535C1 |
| RADIAL-FLOW TURBINE DIRECTIVE NOZZLE DIAPHRAGM WITH VARIABLE INCIDENCE, IN PARTICULAR TURBINES OF ADDITIONAL POWER SOURCE | 2012 |
|
RU2632061C2 |
| BOAT WITH TWO PROPELLERS FOR OBTAINING HIGH AIR PRESSURE | 2023 |
|
RU2823963C1 |
