| 摘要 |
<p>PURPOSE:To improve performance in a high subsonic range by reducing once to angle of the warping line of a diffuser vane to the tangential line to the curved line at the intersection of circle around the rotating shaft of an impeller until it reaches the position on the extension of a straight line which connects the shortest distance from the leading edge of a diffuser vane to an adjacent diffuser vane surface. CONSTITUTION:In a flow rate higher than that of a design condition, flow approaches a diffuser vane 2 from a direction nearer to a radial direction than the extension of the warping line 4 of the diffuser vane 2 as seen in a flow 3a, and in a lower rate lower than that, the flow approaches the diffuser vane 2 from the direction farther from a radial direction than the extension of the warping line 4 as seen in the flow 3b. An angle alpha of the warping line 4 of the end of the diffuser vane 2 to the tangential line of a circle around the rotating shaft of an impeller 1 is so constituted that it may be alpha1>alpha2, alpha3>alpha2 in the extension of the width AB of a throat part which is the shortest distance between the leading edge A of the vane adjacent to the side of the leading edge and a negative pressure surface 2a and the negative pressure surface 2a. It in thus possible to maintain high performance in a wide flow rate range.</p> |
