A kind of aerodynamic design method of subsonic adsorption axial flow compressor
A technology of axial flow compressor and aerodynamic design, applied in mechanical equipment, machines/engines, non-variable pumps, etc., can solve problems such as increased blade rotation angle, difficult suction pipeline layout, separated flow, etc., to ensure high efficiency Effect of flow, avoidance blade strength and suction structure design
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[0020] For the axial compressor stage whose inlet relative velocity is subsonic speed, in conventional design, the axial velocity of the rotor blade inlet, rotor blade outlet and stator blade outlet are usually equal or not changed much. Under the premise that the inlet velocity triangle of the rotor remains unchanged, as the stage load increases to a certain level, the boundary layer flow separation will occur inside the rotor. At this time, by increasing the contraction amplitude of the meridian channel, the axial velocity of the rotor blade outlet is increased to reduce the reverse pressure gradient of the gas in the rotor blade, avoiding the separation flow of the surface layer in the rotor blade and improving the gas flow efficiency in the rotor blade. From a one-dimensional point of view, the method for determining the value of the increase in the axial velocity of the outlet is as follows:
[0021] D = 1 - w 2 w 1 + Δ w u 2 τ w ...
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