EXHAUST SYSTEM OF TURBOPROP ENGINE Russian patent published in 2003 - IPC

FIELD: exhaust aircraft systems of turboprop engines. SUBSTANCE: proposed exhaust system includes exhaust bent pipe evacuating exhaust jet downward and aside; this pipe is secured on aircraft beam and is not brought in contact with engine. Exhaust pipe has inner pipe with exhaust nozzle and shell secured on it in front portion. Nozzle and shell are interconnected by means of detachable casing, thus forming external loop of exhaust pipe which forms in its turn clearance between inner pipe for passage of part of cooling air under action of ejector. Ejector is formed by inner pipe and exhaust nozzle; its rear shear projects beyond rear shear of inner pipe by half its diameter. Under action of other ejector formed by mixing exhaust nozzle fitted on engine and front end of inner pipe moved on it at circular clearance; other part of air is sucked into inner pipe lowering its temperature. Exhaust pipe is secured on external wall of beam and is strengthened by two rods. Inner pipe is connected with shell and exhaust nozzle by means of trapezoidal profiles. One row of these profiles is secured by welding to both members at preliminary pressing. Second row of profiles is welded to inner pipe only at clearance as far as exhaust nozzle. EFFECT: intensification of cooling of exhaust pipe. 4 dwg