The application discloses a tubular vortex
reducer and an aero-engine, and aims at weakening the
vibration problem existing in the tubular vortex
reducer, improving the stability and the drag reduction effect. The technical scheme is as follows: the tubular vortex
reducer comprises a vortex reduction
pipe, a support ring and a damping sheet. The vortex reduction
pipe is arranged in the installation hole of the support ring and is fixed by a clamping ring, is used for guiding the
airflow to flow to the shaft center from the air inlet hole on the first stage disc; the support ring is a hollow annular structure, is coaxial with the rotor disc, and is used for installing the vortex reduction
pipe; the clamping ring is used for fixing the bottom of the vortex reduction pipe between the clamping ring and the support ring, and prevents the vortex reduction pipe from moving along the installation hole to the shaft center of the support ring; the damping sheet is a circular arc
sheet structure, is sleeved into the top of the vortex reduction pipe during installation, the center of the damping sheet is provided with a circular hole with the same
diameter as the outer cylindrical surface of the vortex reduction pipe, the
radial position of the annular damping structure relative to the vortex reduction pipe is set by setting the circular arc
radius of the damping sheet; and the
fastener is used for fixing the support ring and connecting the damping sheet.