FIELD: internal combustion engines.
SUBSTANCE: front part of aircraft double-flow gas turbine engine comprises fan, surrounded by fan casing, reduction gear, rotating fan, units drives unit, as well as mechanical power take-off box. Mechanical power take-off box drives the units drive box. Front part of gas turbine engine also comprises first gear wheel and second gear wheel, which is part of mechanical power take-off box and driven by first tooth-wheel. First gear wheel is made with possibility of forced rotation with fan hub. Front part comprises multiple units, among which is unit that provides oil supply to reduction gear, at that, units are driven into rotation by gearboxes of units. Multiple units, as well as gearbox units are located in inter-loop compartment of gas turbine engine. Another invention of the group relates to an aircraft double-flow gas turbine engine comprising said front part.
EFFECT: group of inventions makes it possible to increase reliability of engine due to possibility of lubrication of reduction gear at autorotation of fan.
8 cl, 12 dwg
