FIELD: engines and pumps.
SUBSTANCE: in propeller fan with annular gas channel there located are hollow posts with through longitudinal slot on outlet edge and with inner cavity in which shanks of blades of propeller fan are arranged; inner cavity of hollow posts, which is made in the form of profile of rotating blades of turbine with inlet and outlet edges, is connected to compressor; at that, on the side of inlet edge of hollow post there is additional zigzag-shaped slot; posts consist of separate segments the number of which is equal to the number of blades of propeller fan, and joint between segments forms longitudinal through slots on the side of inlet and outlet edges of hollow posts; at that, there are seals on outer side from annular gas channel between posts and shanks of blades of propeller fan.
EFFECT: improving reliability and efficiency of operation by arranging the cooling of hollow posts and blades of propeller fan and reducing hydraulic losses in gas channel and losses in joints between segments of hollow posts.
7 dwg
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