Boundary layer suction type propeller adopting large and small two-stage blades

Abstract

The invention discloses a boundary layer suction type propeller adopting large and small two-stage blades. The boundary layer suction type propeller is mounted at the tail part of the aircraft; a large rotor and a small rotor are arranged on the thruster, blades of the large rotor adopt low rotating speed, thrust of a main part is generated, and the requirement for the climbing performance of the aircraft is met. the blades of the small rotor rotate at a higher speed, so that the load of the root can be increased, the load of the blades of the propeller is close to an ideal load, and energy contained in downstream airflow of the propeller is weakened to the maximum extent.

Description

technical field [0001] The invention relates to the technical field of aircraft propellers, in particular to a boundary layer suction propeller adopting two-stage large and small blades. Background technique [0002] Since the "Jet Age", air transportation has experienced explosive growth. Prosperous air transportation has promoted the progress of human society, but it has also brought heavy pressure on resources and the environment. The international community has clearly put forward stricter energy consumption and emission requirements, prompting people to explore energy-saving and emission-reduction technologies. A number of studies of Boeing wing-body fusion BWB aircraft, MIT-Cambridge SilentAircraft, and MIT D8 aircraft have shown that BLI may reduce power consumption by 3 to 20% on the basis of existing aircraft technology. Such energy-saving potential could mean a technological revolution for the aviation industry. [0003] Boundary Layer Ingestion BLI (Boundary Lay...

AI Technical Summary

Problems solved by technology

[0006] (1), the existing propeller can weaken the energy in the downstream airflow by adjusting the blade load distribution along the radial direction, however, the rotational speed of the blade root is much lower than the tip speed, it is difficult (at the root) The axial momentum is greatly increased to achieve the ideal energy-saving effect

[0007] (2) There are vortices that naturally fall off at the root of the propeller blade, such as the horseshoe vortex at the root of the fan blade and the vortex at the root of the propeller blade. The existing propeller, by adjusting the load distribution of the blade, adopts a large load (circulation) at the root of the blade The design may induce an increase in blade root vortex strength, causing airflow separation at the blade root, thereby significantly increasing power consumption

[0008] (3) Intake distortion problem, because the airflow inhaled by the propeller contains boundary layer airflow, the uneven incoming flow causes intake distortion, which poses a safety hazard to the rotating propeller blades

Images