REDUCTION GEAR WITH TWO INTERMEDIATE LINES FOR TURBO-PROPELLER ENGINE, TURBO-PROPELLER ENGINE COMPRISING SAID REDUCTION GEAR Russian patent published in 2020 - IPC F16H1/22 F16H1/48 

FIELD: aircraft engineering.

SUBSTANCE: reduction gear with two intermediate lines for a turboprop engine comprises an input line comprising an input shaft with an input gear installed on it, a first intermediate line, comprising a first intermediate shaft with a first intermediate gear mounted thereon, a second intermediate line comprising a second countershaft with a second idler installed thereon, spring fixed on support. Spring surrounds longitudinal section of input shaft to ensure movement of input gear to equilibrium position, corresponding to equal distribution of power transfer, supplied from input shaft, to first intermediate shaft of first intermediate line and to second intermediate shaft of second intermediate line. Turbo-propeller engine comprising said reduction gear is also claimed.

EFFECT: improved distribution of loads of two intermediate lines of reduction gear.

11 cl, 5 dwg