The invention discloses a novel
nozzle and fin combined type vortex reduction
system, and relates to aero-engines. The novel
nozzle and fin combined type vortex reduction
system comprises a plurality of reverse rotation nozzles and a plurality of reverse rotation fins, each reverse rotation
nozzle is installed at the position of a two-stage
gas compressor disc, and each reverse rotation fin is installed at the position of a front-stage
gas compressor disc and located at the downstream position of the multiple reverse rotation nozzles; the reverse-rotation nozzles and the reverse-rotation fins are evenly arranged in the circumferential direction of the
gas compressor discs and are coaxial with the gas compressor discs on the two sides, the structures of the reverse-rotation nozzles and the reverse-rotation fins are the same, the corresponding installation radiuses are the same, the circumferential speed of
airflow is limited, development of free vortexes is restrained, and flow hindrance is reduced. Compared with a vortex reducing
pipe, the flow area of the reverse rotation fins is large, sudden expansion and sudden shrinkage of a flow channel in the air entraining process are avoided, therefore
viscous dissipation caused by
airflow mixing is reduced, and
airflow total pressure losses are reduced.