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美国政府科技报告
>EFFECT OF BLADE-THICKNESS TAPER ON AXIAL-VELOCITY DISTRIBUTION AT THE LEADING EDGE OF AN ENTRANCE ROTOR-BLADE ROW WITH AXIAL INLET, AND THE INFLUENCE OF THIS DISTRIBUTION ON ALINEMENT OF THE ROTOR BLADE FOR ZERO ANGLE OF ATTACK
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EFFECT OF BLADE-THICKNESS TAPER ON AXIAL-VELOCITY DISTRIBUTION AT THE LEADING EDGE OF AN ENTRANCE ROTOR-BLADE ROW WITH AXIAL INLET, AND THE INFLUENCE OF THIS DISTRIBUTION ON ALINEMENT OF THE ROTOR BLADE FOR ZERO ANGLE OF ATTACK
A method is developed for estimating the effect of blade-thickness taper on the inlet axial-velocity distribution of an entrance rotor-blade row with axial inlet, and the influence of this velocity dis¬tribution on the alinement of the rotor blade for zero effective angle of attack (that is, zero blade loading at the nose). This alinement of the blade requires a deviation between the angle of the blade camber line direction at the inlet and the upstream relative flow direc-tion. The method is developed for compressible and incompressible non-viscous fluids, and results are presented for incompressible flow into a plane, two-dimensional cascade and for compressible flow into an entrance rotor-blade row with tapered blades. It is concluded that, for the entrance rotor-blade row investigated, blade taper has a large effect on the inlet deviation angle;whereas compressibility has a small effect, except perhaps at the hub, and the upstream relative flow direction also has a small effect.
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