| 摘要 |
mechanical engineering; aircraft engines. SUBSTANCE: invention relates to turbojet engine with reheat unit and rotating reaction nozzle with control and adjustment system installed on modern highly maneuverable aircraft and multi-mission fighters. Owing to bypassing part of fuel from peripheral nozzle manifold into low-pressure space, according to actual position of links of rotating nozzle drive mechanism relative to initial position in proportion to its turning angle, temperature of near-wall layer of gas flowing over cooled walls of nozzle decreases. It is provided owing to the fact that bypass valve is installed on high-pressure fuel feed line to peripheral nozzles of reheat unit. Said valve is secured on engine and is mechanically coupled with power drive and hydraulically connected by its input to fuel feed manifold and by its output, to low-pressure fuel system. EFFECT: improved reliability of rotating nozzle at modes with changeable direction of thrust vector by decreasing heat flows to cooled walls of nozzle. 1 dwg
|
