FIELD: aircraft engines.
SUBSTANCE: the aircraft gas-turbine engine assembly has an interturbine frame positioned in the axis between the high-pressure and low-pressure turbines. The low-pressure turbine has oppositely revolving inner and outer low-pressure rotors with inner and outer low-pressure shafts, which at least partially are positioned for revolution coaxially with the high-pressure rotor and inside it. The interturbine frame has the first and second constructional rings being apart from each other in the radial direction, they are positioned in the axial direction coaxially about the central line and coupled by means of a great number of posts distributed in the circular direction of the posts. The members of the front and rear sumps, having the front and rear central ducts, are fixed to the front and rear parts of the interturbine frame being apart from each other in the axial direction. The low-pressure rotors rest for revolution on the second bearing of the turbine frame installed in the rear central duct of the member of the rear post. The mounting support is positioned on the first constructional ring for coupling of the engine to the aircraft.
EFFECT: reduced length of the engine assembly, weight and cost, provided low loss of the clearance on the blade tips.
14 cl, 10 dwg
