Improvements in rotary compressors

Abstract

Abstract 479,427. Centrifugal and axial - fiow compressors. JENDRASSIK, G. May 29, 1936, No. 15192. Convention date, May 31, 1935. [Class 110 (i)] Axial-flow or radial-flow turbo - compressors with working and guiding rows of blades have the blade carriers formed with channels to conduct the boundary layer of gas from higher to lower pressure regions, the channels having discharge orifices formed to give the returning gas a direction component the same as that of the main flow. The inlet orifices may be directed perpendicular to or against the main flow. The channel outlets have a smaller area than the inlets, and the channels in any one stage have a smaller area than those in a higher-pressure stage. The guide blades may rotate or be stationary, and there may be two or more successive rows of rotating or stationary blades. The channels 68, Fig. 9, of the rotor 56 are formed under rings 58 carrying the rotor-blades 60 and clamped by rings 57 having channels and boundary rings 59. The guide-blades 61 are carried by rings 63 which with the rings 64 are grooved to form the channels 69 with boundary rings 65, all these rings being carried by member 62 which may rotate or be stationary. The channels may be formed by annular grooves in the casing walls with the rotor-blades projecting into the grooves. The free ends of the blades 83, Fig. 12, may be riveted to a crown-ring 86 which may carry auxiliary blades 87. The channels may have guide vanes 88, carried by the rings 81, 82 to increase the velocity of the returning gas. The rise of pressure within any row of blades may be dirninished without risk of detachment by subdividing the blades into several rows, or into one row, Fig. 8, with split profiles having one or more splits. The guide-vanes may be adjustable so as to contribute either a rise or a drop in the pressure or to keep the pressure unchanged. The Specification as open to inspection under Sect. 91 states also that to enable each blade to produce the same pressure in each of its portions, it is made narrower in the centre than at its ends and it is also centrally twisted to obtain a more favourable angle of impact with respect to the velocity at that portion. In Fig. 16 (Cancelled), a rotor-blade and a guideblade are shown in section at A on a central line and at B and C at their ends. The angle alpha<1> is greater than the angles alpha<2>, alpha<3> and the width t<1> less than the widths t<2>, t<3>. This subject-matter does not appear in the Specification as accepted.

Inventors

No inventors recorded.

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