RU2557818C1 - Radial-swirl turbo-machine - Google Patents

Abstract

FIELD: machine building.

SUBSTANCE: turbo-machine contains spiral casing, installed in it impeller, carrying and covering disks located between them bend backwards shaped shoulder blades (5). Each blade (5) is equipped with the flap (8) installed with converging clearance (6) in relation to its work surface (7), the flap has concave work and convex end surfaces (9, 10), and have vortex chamber (11) connected tangentially with clearance (6), output converging channels (12) on its surface (10) from chamber (11), and output converging channels (13) with tangential input in it from surface (9) of the flap (8). In the spiral casing on the carrying disk in the vortex chamber (11) of each flap (8) the tangential input converging channel (14) is made, and on the coverage disk from the vortex chamber (11) a tangential output converging channel (15) is made.

EFFECT: increased aerodynamic loading of the radial vortex turbo-machine due to increased kinetic energy of the flow rotation in the vortex chamber by means of creation of the high energy vortex core, and as result the increased pressure difference between the work and rear surfaces of the blades.

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Description

The invention relates to the field of turbomachines, in particular to radial fans, pumps, compressors.

Known radial vortex turbomachine containing a spiral casing, an impeller installed in it with a bearing, cover discs and blades located between them, having longitudinal and additional protrusions on the working and rear surfaces in the area of the output part, forming an annular cylindrical vortex in the region of the trailing edge of the blade a camera mounted on a carrier and cover discs, with an axis parallel to the trailing edge of the blade, a tangential inlet channel from the side of its working surface and perforated the surface of the cylindrical shell, installed with a gap so that the tangent to it along the line of intersection of the plane passing through the axis of the chamber and the trailing edge of the blade is parallel to the tangent to the working and back surfaces of the blade on its trailing edge (Patent 2430274 (Russia). Cl. F04D 29/28. Radial-vortex turbomachine / Kosarev NP, Makarov NV, Makarov VN, publ. 09/27/2011).

This design of the blade of the impeller of a radial vortex turbomachine contributes to the flow of a part representing the control flow from the interscapular channel of the impeller through the tangential inlet channel to the vortex chamber and twists it in the direction of rotation of the impeller. The perforated surface of the annular cylindrical vortex chamber provides an efficient transfer of the circulation energy of the control flow to the main stream in the interscapular channel of the impeller, helping to increase the angle of rotation around the cylindrical shell of the vortex chamber, i.e., the angle of exit of the flow from the impeller. This contributes to the increase in pressure developed by the radial-vortex turbomachine, that is, its aerodynamic loading.

However, the low level of rotational energy of the control flow makes it possible to slightly increase the angle of exit of the flow from the impeller of the turbomachine, which leads to an insufficient increase in the pressure developed by the radial-vortex turbomachine, i.e. its aerodynamic loading.

The closest in execution to the proposed technical solution is a radial-vortex turbomachine, containing a spiral casing, an impeller installed in it with a bearing and cover discs, profile blades located between them, each of which is equipped with a confuser gap installed in the outlet area relative to its working surface with a cover with a concave working, convex end surfaces and having a vortex chamber communicating tangentially with the confuser gap, confuser channels to its convex end surface from the vortex chamber and inlet confuser channels with a tangential entry into it from the concave working surface of the cover (Patent 2525037 (Russia). Cl. F04D 29/28. Impeller of a centrifugal fan. Kosarev NP, Makarov N.V., Makarov V.N., publ. 04/08/2014).

This design scheme due to the additional supply of the control flow from the interscapular channels to the vortex chambers through the inlet confuser channels partially eliminates the disadvantages of the previously described design, i.e. increases the aerodynamic loading of a radial vortex turbomachine.

However, this embodiment of the output part of the backward-curved profile blade of the impeller of a radial-vortex turbomachine does not fully provide the increase in the energy of rotation of the control flow swirling in the vortex chamber, and improves the structure of the main flow on the working concave surface of the lining, which does not significantly increase the aerodynamic loading of the radially a vortex turbomachine, since it does not provide a significant increase in the pressure drop of the flow between the working and back surfaces of the blade.

The objective of the invention is to increase the aerodynamic loading of a radial vortex turbomachine due to a significant increase in the kinetic energy of rotation of the control flow swirling in the vortex chamber, that is, the formation of a high-energy "vortex tourniquet", its impact on the main flow on the convex end and concave working surfaces of the blade lining, thereby increasing the angle of exit of the flow from the impeller and the pressure drop of the flow between the working and back surfaces of the blade.

The technical result is achieved by the fact that in the proposed radial-vortex turbomachine, comprising a spiral casing, an impeller installed therein, a bearing and a cover disc, profile blades located between them, each of which is provided in the outlet area with a confuser gap set in relation to to its working surface with a lining with a concave working, convex end surfaces and having a vortex chamber communicating tangentially with a confuser gap, outlet confuser channels and its convex end surface from the vortex chamber and inlet confuser channels with a tangential entry into it from the concave working surface of the napkin, according to the invention, in the spiral housing on the carrier disk into the vortex chamber of each napkin, a tangential entrance confuser channel is made, and on the cover disk of each vortex chamber the lining is made tangential output confuser channel.

In FIG. 1 shows a cross section of a radial vortex turbomachine. In FIG. 2 shows a longitudinal section through a radial vortex turbomachine. In FIG. 3 shows the inlet of a backward curved profile blade with a wing. In FIG. 4 shows section AA in FIG. 2. In FIG. 5 shows a section BB in FIG. 2.

The radial vortex turbomachine contains a spiral casing 1, an impeller 2 installed therein, bearing 3 and a cover 4 discs, profile blades 5 located between them, each of which in the outlet part area is equipped with a confuser gap 6 with respect to its working surface 7 of the cover 8 with a concave working 9, convex end surfaces 10 and having a vortex chamber 11, communicating tangentially with confuser gap 6, outlet confuser channels 12 to its convex end surface 10 of the vortices evy chamber 11 and inlet confuser channels 13 with a tangential entrance into it from the concave working surface 9 of the wing 8. In a spiral casing 1 on the carrier disk 3 in the vortex chamber 11 of each wing 8 there is a tangential inlet confuser channel 14, and on the cover disk of the vortex chamber 11 each wing 8 is made tangential output confuser channel 15.

When the impeller 2 of the radial vortex turbomachine rotates, the air flow entering the interscapular channels formed by the supporting 3, cover 4 discs and blades 5, interacting with the latter, rotates in the direction of rotation of the wheel 2 along the working surfaces 8, 9 of the blades 5 and their wings 8 The part of the flow, which is a control flow, due to the pressure difference between the working 9 and the back 10 surfaces of the wing 8 of the blade 5 through the tangential inlet of the confuser gap 6 enters in the tangential direction in the vortex chamber eru 11, spinning in it at a speed exceeding the speed of rotation of the impeller 2. Due to the excess pressure on the working concave surface 9 of the cover 8 with respect to the pressure in the vortex chamber 11, a part of the flow from the interscapular channel through the inlet confuser channels 13 is tangential, i.e. tangent, enters the vortex chamber 11, further increasing the rotation energy of the control flow.

Under the action of excess pressure in the inlet confuser channel 14 and rarefaction in the outlet confuser channel 15, due to increased pressure in the spiral casing 1, rotation of the impeller 2 and the ejection effect, a stable, high-energy “vortex rope” is created in the vortex chamber 11, which significantly increases the energy rotation of the control stream.

Due to the centrifugal force of rotation, the high-energy control flow through the outlet confuser channels 12 enters the rear surface 10 of the lid 8 of the blade 5 of the impeller 2, helping to eliminate the area of separation vortex formation, and, as a result, a significant increase in the angle of exit of the main flow from the impeller 2 and, accordingly, provides a significant increase in the pressure drop between the working and back surfaces of the scapula. As a result of this, there is a significant increase in the aerodynamic loading of the radial vortex turbomachine.

The suction of a part of the flow from the interscapular channel on the working concave surface 9 of the wing 8 through the inlet confuser channels 13 due to the high-energy “vortex bundle” leads to an improvement in the structure of the main flow on the working concave surface 9 of the wing 8, reducing the flow rate on the working surface 9 of the wing 8 of the blade 5 , contributing to an increase in pressure on it due to the Magnus effect, that is, an increase in the pressure drop between the working 9 and rear 10 surfaces of the wing 8 of the blade 5, which increases the aerodynamic load for alno-vortex turbomachine.

The synergistic effect of increasing the angle of exit of the main stream from the impeller 2 and increasing the pressure drop between the working 9 and rear 10 surfaces of the wing 8 of the blade 5 due to the formation of a high-energy “vortex bundle” significantly increases the rotation energy of the control flow, leading to a significant increase in the aerodynamic load of the radial vortex turbomachines.

According to the test results of a radial vortex-type fan of the above design with tangential inlet and outlet channels of the vortex chambers located on the rotor and casing disks of the impeller connecting them to the cavity of the spiral casing of the radial-vortex turbomachine, an increase in pressure coefficient of 12% is obtained in comparison with the prototype, that is, up to the value ψ = 1.88.

Thus, the use of this design of a radial-vortex turbomachine can effectively eliminate the tear-off vortex formation on the back of the blade, increase the angle of rotation of the flow at the exit of the impeller and the pressure drop between the working and back surfaces of the blade, which significantly increases the aerodynamic loading of the radial-vortex turbomachine.

Claims (1)

A radial vortex turbomachine containing a spiral casing, an impeller installed in it, a bearing and cover discs, profile vanes located between them, each bent in the outlet area, is equipped with a cover with a concave working flap installed with a confuser gap with respect to its working surface convex end surfaces and having a vortex chamber communicating tangentially with a confuser gap, outlet confuser channels to its convex end surface from the vortex chamber and inlet confuser channels with a tangential entrance to it from the concave working surface of the napkin, characterized in that a tangential inlet confuser channel is made in the spiral housing on the carrier disk into the vortex chamber of each napkin, and a tangential output confuser channel is made from the vortex chamber of each napkin on the cover disk. .

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