ROTATING ROUND AXIS SYMMETRIC JET NOZZLE OF AIRCRAFT JET ENGINE Russian patent published in 2008 - IPC F02K1/06 

FIELD: invention refers to engine building.

SUBSTANCE: rotating round axis symmetric jet nozzle of aircraft jet engine has body of nozzle, rotating arrangement of nozzle in shape of two mobile rings, external and inner, and four hydraulic cylinders controlling vector of thrust and four pneumatic cylinders. Body of nozzle consists of located along flow of unmovable and mobile parts. Hydraulic cylinders controlling vector of thrust are located in pairs in two diametrically opposed points in vertical and horizontally longitudinal planes. Pneumatic cylinders are located in pairs in two diametrically opposed points and each pair of pneumatic cylinders is located between hydraulic cylinders under angle of 45 degrees to vertical and horizontal longitudinal planes. Piston and rod cavities of each pneumatic cylinder have hollow windows for feeding of compressed air and hollow windows in middle of body of pneumatic cylinder for discharging air. Square of passing section of the last is larger then square of passing section of the first and at traveling of piston of pneumatic cylinder into neutral middle position its lateral surface completely covers passing sections of windows for discharging air. From face rod side of at least of one of four pneumatic cylinder there is locking valve, which includes in itself body with located inside it spring-actuated piston with rod. Free end of rod of locking valve in neutral middle position of piston of pneumatic cylinder enters into ring groove, fulfilled on rod of pneumatic cylinder. Body of locking valve has pipe connections for feeding of compressed air into rod cavity of locking valve and through hollow window into rod cavity of pneumatic cylinder on which locking valve is installed. Invention allows ensure reliable work of nozzle with changing direction of vector of thrust and resetting nozzle in axis symmetric position in case of failure of standard system for control over vector of thrust.

EFFECT: ensures reliable work of nozzle.

8 dwg