FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engineering, namely to reversible thrust devices for gas turbine engines located in the tail section of an aircraft. During reverse operation, the air in the outer contour of the engines is partially or completely blocked by a system of folding flaps and removed from the engine through radial channels opened by moving back the tail parts of the outer shell rigidly connected to the upper and lower skins of the engine pylons. The radial channels are closed by an inflatable fabric shell laid under the sliding parts of the outer shell and the upper and lower skins of the pylons, which, in the inflated state, has a toroidal configuration, enclosing each engine in the circumferential direction with discharge sleeves passing along the upper and lower surfaces of the pylons into the aircraft fuselage through hatches, opened by sliding skins of the pylons. The sleeves are connected to an internal air duct laid along the fuselage to the side and reverse thrust nozzles. The reverse thrust nozzle is located in the upper part of the fuselage and is extended into the oncoming air flow by a lifting lever.
EFFECT: invention provides increased efficiency of thrust reverser by increasing the angle of deflection of the reversed flow without throwing the jet at the engine inlet and preventing the ingress of foreign objects from the runway surface into the engine.
6 cl, 11 dwg
