GB586726A - Superchargers - Google Patents

Abstract

586,726. Centrifugal compressors. BENDIX AVIATION CORPORATION. May 17, 1944, No. 9494. Convention date, April 13, 1943. [Class 110 (i)] The impeller of a centrifugal compressor is formed with two sets of passages extending from inlet eyes on opposite sides to separate outlet zones, at the periphery, the two sets crossing one another in the impeller body. In the two-stage compressor shown air passes successively through the two sets of passages 52, 54, the latter set projecting slightly beyond the former to reduce leakage and increase presure. The air inlet 38, strengthened by a web or webs 40, leads to an annular manifold which communicates with the inlet to the passages 52 through a ring of guide vanes 44. Air leaving the passages 52 passes through sets of vanes 62, 68, to straighten the flow, to the inlet to passages 54 in the impeller, the.passage between stages acting as an intercooler ; the hollow in the part 64 may be in communication with the atmosphere through an opening in one of the vanes 68. Further vanes 62 straighten the flow of air from the impeller passages 54 on the way to the discharge volute and outlet passage 72. The impeller is mounted on a hollow shaft supported in ball-bearings, the free end being covered by a cap with lubricant passages 26. An air passage 76 may be provided to prevent lubricant from being sucked into the intake passages, and passages 78 may be provided where required to equalise pressures so as to minimise leakage.