FIELD: transport.
SUBSTANCE: set of inventions relates to the airscrew blade pitch adjustment system for aircraft gas turbine engine. Proposed system comprises the following components that follow: first race coupled with airscrew blade to allow setting the angle of attack of said blade in rotation and second race, drive element 60 for first race arranged between said and second races and having the section with angular recesses. Besides, it has, at least, one locking element 64 arranged between said first and second races at said section with angular recess of drive element in V-like groove of the first race. Element 64 can seat at normal centered element to drive simultaneously said first and second race and at unlocking position to allow shift in rotation of assembly including first race, element 64 and element 60.
EFFECT: simplified design, no use of separate locking mechanism, decreased weight, higher reliability.
17 cl, 7 dwg
