The invention discloses a novel combined type vortex-reducing device air guiding system for an aero-engine. The novel combined type vortex-reducing device air guiding system comprises a gas compressorfront disc cavity, a gas compressor rear disc cavity and a novel vortex-reducing device structure which are used for forming a gas compressor disc cavity, the novel vortex-reducing device structure comprises a first vortex-reducing disc, a second vortex-reducing disc and a plurality of pipes, fins or separating plates, wherein the plurality of pipes, the fins or the separating plates are arrangedbetween the first vortex-reducing disc and the second vortex-reducing disc, the pipes, the fins or the separating plates are uniformly distributed in the vortex-reducing disc in the circumferential direction, and the installation number and arrangement mode of the pipes, the fins and the separating plates are unlimited. According to the novel combined type vortex-reducing device air guiding system, the integral type vortex-reducing structure is adopted, so that the arrangement of the pipes, the fins or the separating plate mounting positions is facilitated, and machining and installation areconvenient; and by adopting the composite installation of the pipes, the fins or the separating plates, the vibration defect in the operation process of a single pipe type vortex-reducing device can be overcome, the pressure loss of the vortex-reducing device air guiding system can be effectively reduced, and the air supply capacity of the cooling air of a secondary air system of the aero-engine is guaranteed.