FIELD: engines and pumps.
SUBSTANCE: invention relates to aviation engines building and can be used in assembly of turbofan engine fan impeller. Technical result is achieved by fact that actual value of controllable parameter of all produced blades engine range, sorted for with monotonous variation of controlled parameter is divided into multiple blades into groups according to number of blades in impeller, calculated actual range tolerance of controllable parameter of blades in each group. For a group with highest value of allowance is used to calculate aircraft noise level reduction in points where it is normalised at takeoff and climb, determined as difference between aircraft noise levels with motors having standard tolerance for the installation angle of impeller blades, and noise levels of aircraft with engines with impeller vanes have maximum value range of access; in case of insufficient value reduction of noise level at check points at takeoff and climb re-sorted blades between groups, reducing value range of access inside group, after that repeated calculation and re-sorting until maximum possible reduction of noise level, then blades of each group in impeller at first half of circle in ascending order of controlled parameter, and second half-circle in order of its order or vice versa.
EFFECT: technical result is reduction of noise levels of aircraft at takeoff and climb at control points at ICAO standards.
2 cl, 7 dwg, 1 tbl
