Anti-distortion stator design method suitable for contra-rotating lift propulsion device

Abstract

The invention discloses an anti-distortion stator design method suitable for a contra-rotating lift propulsion device. The anti-distortion stator design method mainly aims at a blade profile of an area with the blade height being 55% or above in original stator design. Multi-structure parameter distribution such as front / tail edge radius distribution, mounting angle distribution, chord length axial projection distribution, mean camber line length distribution and maximum thickness distribution of a local stator is subjected to coupling analysis, the blade profile is reconstructed, and an anti-distortion stator area is reasonably arranged according to a distortion range to change local distortion propagation characteristics of a stator. The method has the effects of inhibiting the circumferential nonuniformity of a second-stage rotor inlet flow field of the lift propulsion device, the unsteady effect of various flow field parameters of a second-stage rotor inlet and the wake effect of afirst-stage stator, and meanwhile, the stator structure has no harmful influence on an aerodynamic steady performance curve of a lift fan. In addition, the method has certain simplicity in design andprocessing, and has the potential of actual engineering popularization and application.

Description

technical field [0001] The invention relates to the field of aviation vehicle design, in particular to an anti-distortion stator design method suitable for a counter-rotating lift propulsion device, which is suitable for the hybrid aircraft lift propulsion device in the start-up stage when it faces baffle shielding or encounters gusts of wind during flight. Background technique [0002] The counter-rotating lift fan is an important power device of the future hybrid aircraft, and its stability directly determines the maneuverability of the aircraft and the safety of the take-off and landing process. Because hybrid aircraft are mostly used in remote mountainous areas, oceanic islands and reefs, and aircraft carriers where the surrounding airflow is relatively turbulent, the stability of their lift fans is often threatened. In addition, the threat is exacerbated by the locally distorted flow field induced by the opening of the lift fan's shield hatch during the start-up process...

AI Technical Summary

Problems solved by technology

[0005] However, most of the above studies are based on single-stage turbomachinery. Since there is a significant reaction of the second stage to the first stage in more stage turbomachinery (especially for counter-rotating lift fans with reversed rotors in the second stage), it is aimed at the single-stage turbomachinery. The results of the study may be at risk of invalidation

In addition, most of the corresponding asymmetric layouts in the above studies only start from the basic parameters such as the number of local blades and the installation angle of local blades, and rarely couple multiple geometric parameters to redesign the blade configuration.

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