FIELD: engines and pumps.
SUBSTANCE: aircraft gas turbine engine containing a fan and a compressor, which are made of composite material. So, the impellers of the fan and the compressor are made of composite material, wherein the blades are made monolithically with the support ring, which, in turn, is connected monolithically to the front and rear flanges. The blades are provided with shanks which are inseparably connected to the support ring and to the inner surfaces of the front and rear flanges. Also, the entrance edge of the blade is protected by a metal lining, which is clamped by the blade shank, the inner surface of the front flange and the interblade fastening.
EFFECT: invention allows to reduce the specific gravity and complexity of product manufacture.
10 dwg
