SU1413252A2 - Vortex machine - Google Patents

Abstract

The invention relates to a turbomachine structure and allows an increase in the efficiency of the machine. The working annular channel (CC) 2 in the radial section has the shape of a circle. The peripheral edge of each blade 7 of the impeller 6 is inclined towards the wheel and is located relative to the radial plane passing through) without the edge of the edge located on the side of the inlet nozzle (VP) 3 at an angle Y arctg (0.135-0.285). The axis of the EP is shifted relative to the plane of symmetry of the spacecraft, located normally to the ax of the impeller, by an amount A determined by the inequality., 34d; (1,3-P - / Fit), where FC is the cross-sectional area of the VP at the exit; FK is the radial section of QC. With this design, the working body enters the blades with minimal impact losses and organizes a stable vortex motion along the entire length of CK-4 sludge.

Description

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This invention relates to a turbomachine structure, in particular, to vortex machines.

The aim of the invention is to increase efficiency.

FIG. 1 shows a vortex machine; in fig. 2 is a section A-A in FIG. one; in fig. 3 is a section BB in FIG. one; in fig. 4 is a view of B in FIG. 3

The vortex machine includes a housing 1 with a working annular channel 2, inlet and outlet nozzles 3 and 4, a cutter 5 between the latter in channel 2, and an impeller 6 placed in the housing with cantilever blades 7 inclined in the direction opposite to the direction of rotation of the wheel 6, and located in the annular channel 2. The axis aa of the inlet nozzle 3 forms, with a tangent bb to the outer diameter d of the impeller 6, an angle of 30-50 °, and an angle p of the inclination of each blade 7 to the radial plane passing through its base in equals 35 °. The working annular channel 2 in the radial section has the shape of a circle, the peripheral edge of each blade 7 is inclined in the direction of rotation of the wheel 6 and is located relative to the radial plane in-in, passing through the edge of this edge, displaced from the inlet nozzle, at an angle Y arctg (0.135 -0,285), and the axis a-a of the inlet nozzle is offset by the value of A relative to the plane r-d symmetry of the annular channel 2, located normally to the axis of the impeller 6, by the value defined by the inequality

, 34V (1.3-1),

0

five

0

five

0

where FC is the cross-sectional area of the inlet nozzle 3 at the outlet;

F, f is the area of the radial section of the annular channel 2.

Vortex machine works as follows.

The working body through the pipe 3 enters the working blades 7 at an angle of 30-50 ° with minimal impact losses, flowed along the blades 7 to the side relative to the plane of g-g symmetry of the annular channel 2, organizes a stable vortex motion along the entire length of the annular channel and, having given the kinematic energy of movement of the impeller 6 is discharged through the nozzle 4.

Claims (1)

Invention Formula Vortex machine auth. St. No. 1260534, characterized in that, in order to increase efficiency, the working annular channel in the radial section has the shape of a circle, the peripheral edge of each blade is tilted in the direction of rotation of the wheel and is located relative to the radial plane passing through the edge of this edge nozzle, at an angle Y arctg (0,135-0,285), and the axis of the inlet nozzle is offset relative to the plane of symmetry of the annular channel, located normally to the axis of the impeller, by an amount determined by the inequality 0 , 34V (1,3-g, where FC is the cross-sectional area of the inlet pipe at the outlet; FX is the area of the radial section of the annular channel. I-A FIG g Bb Type B