초록 ▼

The pitch control mechanism (controlling the angular position) for stator blades in a turbojet may be adjusted separately for two adjacent stages of blades controlled by a common actuator 10. To achieve this, the synchronization bar 9 located between the mechanisms leading to the two stages is incli

The pitch control mechanism (controlling the angular position) for stator blades in a turbojet may be adjusted separately for two adjacent stages of blades controlled by a common actuator 10. To achieve this, the synchronization bar 9 located between the mechanisms leading to the two stages is inclined, this inclination being determined by a pin 22 and groove 23 connection with the casing, while another pin 26 and groove 27 connection is arranged between the synchronization bar 9 and one of the mechanisms. Strongly non-linear displacement laws between the two mechanisms may thus be controlled depending on the shapes and directions of the grooves.

대표청구항 ▼

The invention claimed is: 1. Variable pitch device for two stages of stator blades ( 2), arranged on a casing (1) and provided with an actuator mechanism, and a bellcrank (7, 8) for each stage, pivoting on an axis (20, 21) of the casing and a stage control connecting rod (6) connected to a branch o

The invention claimed is: 1. Variable pitch device for two stages of stator blades ( 2), arranged on a casing (1) and provided with an actuator mechanism, and a bellcrank (7, 8) for each stage, pivoting on an axis (20, 21) of the casing and a stage control connecting rod (6) connected to a branch of the bellcrank, a synchronization bar (9) being connected to another branch of at least one of the bellcranks to displace it, characterized in that the synchronization bar is connected to the casing through a groove connection (23) and a pin (22) sliding in the groove, and to the bellcrank that it displaces by another groove connection (26 ) and a pin (27) sliding in the another groove.