GB1461430A - Compressor having two or more stages - Google Patents

Abstract

1461430 Multi-stage compressor UNITED TURBINE AB & CO KB 29 Nov 1974 51712/74 Headings F1C and FIT [ Also in Division F2] A compressor comprises a centripetal first stage communicating with a centrifugal last stage either directly or via an intermediate axial flow stage, all stages being mounted on a common shaft 11, Fig. 1, the centripetal stage having a maximum radius less than that of the centrifugal stage. The centripetal stage includes vanes 13 mounted on a rotor 12, which direct air radially inwardly into a passage 14 and thence into the centrifugal stage 10 in which the air is directed outwardly towards guide vanes 17 which may be adjustable and coupled to adjustable guide vanes 16 at the inlet to the centripetal stage. Guide vanes 20 are fixed to the wall forming the passage 14 which may be bounded by the centrifugal rotor, Fig. 3 (not shown), and further guide vanes (25) may be provided intermediate the two stages. Water from an annular chamber 16b may be introduced into the compressor through some of the vanes 16 for cleaning purposes or to provide power boosts in a gas turbine engine incorporating the compressor. An axial flow stage 30, Fig. 4, may be situated between the other stages and is surrounded by stator vanes 31, 32, the axial flow stage communicating with passages 33, 34 for sucking away the boundary layer. The vanes 17 may be omitted. Also, the centripetal stage can under certain circumstances operate as a turbine. Shaft 11 is journalled in a compressed air lubricated bearing 36.