FIELD: engines and pumps.
SUBSTANCE: propose mechanism allows separate adjustment of the blades in two adjacent turbojet engine stages controlled by common drive. For this, mechanisms' synchronisation lever 9 comes into an inclined position defined by the link made up of pin 22 and groove 23 coupling the aforesaid lever with the said case. Note that another link made up of pin 26 and groove 27 couples the said lever 9 and one of the aforesaid mechanisms.
EFFECT: non-linear laws of motion between aforesaid two mechanisms can be implemented by appropriate shapes and directions set for mentioned grooves.
5 dwg
