WO2019093576A1 - Impeller having primary blades and secondary blades - Google Patents

Abstract

The present invention comprises: a first portion having a first hub, and a plurality of primary blades extendedly formed at equal intervals along the outer periphery of the first hub; and a second portion having a second hub coupled to the lower side of the first hub in an uneven form, and a plurality of secondary blades extendedly formed at intervals along the outer periphery of the second hub, wherein, when a projection angle between a leading edge (L.E.) and a trailing edge (T.E.) of each primary blade is Φ1, and a projection angle between a leading edge (L.E.) and a trailing edge (T.E.) of each of the plurality of secondary blades is θ1, each angle comprises upstream angles Φ1u and θ1u and downstream angles Φ1d and θ1d at which the primary blades and the secondary blades are respectively overlapped, and angles Φ1m and θ1m at which theprimary blades and the secondary blades are not respectively overlapped, and θ1 is less thanΦ1 such that the radii of the primary blade and the secondary blade satisfy 0 < θ1 <Φ1 from each hub to the tip thereof.

Description

Impeller with main wing and auxiliary wing

The present invention relates to an impeller, and more particularly, to an impeller in which a plurality of secondary blades are disposed between a plurality of primary blades to perform blade flow control.

Studies on the design of fluid machines such as known fans, blowers and pumps have been in the past decades and many advances in design techniques have been made. In recent years, however, as the demand for noise as well as performance has increased, and the size of the product has decreased, it has become necessary to develop more advanced design means.

Conventional axial impellers applied to fluid machinery exhibit their performance at pressure and flow rates. Specifically, as shown in FIG. 1, the pressure difference? P at the inlet and the outlet increases as the fluid flows between the blades 1, and the pressure is increased by the lift of the blades as the streamlines are bent along the curvature of the blades. Therefore, as the wire is bent along the wing camber wire 3, a rotational speed component is generated, which is advantageous for increasing the pressure.

However, wired (stream line) corresponding to this if too much bend "As you at an angle of α _2, unlike the α ₂ -α ₂ 'in the wing negative pressure side flow separation also α ₂ of the rear end (TE) blade angle (= δ) difference A deviation angle is generated. The deviation angle δ is a function of the aspect ratio (σ = C / s), which is the ratio of the camber angle (Φ _c ) of the wing to the wing code (C) and the pitch (s) . That is, as the camber angle? _C increases, the deviation angle increases. When the aspect ratio, that is, the wing code, increases, the deviation angle decreases and the performance increases.

Where δ ₀ is the airfoil shape, m ₀ is the stiffness ratio, and b is a constant determined by the inlet flow angle α ₁ .

The prior art has focused on increasing the camber angle without increasing the flow separation, causing a large pressure rise through lift, increasing the cord length or reducing the blade pitch by reducing the blade pitch to reduce the exit angle . However, if the cord is lengthened, the impeller becomes higher in the direction of the rotating shaft, and the camber angle for increasing the pressure is limited by the flow separation at the negative pressure surface.

U.S. Patent Publication No. US 2014/0233178 A1 discloses an example in which the auxiliary wing is started near the rear end (T.E.) of the main wing, thereby increasing the aspect ratio by increasing the wing length and increasing the performance by reducing the deviation angle of the wing exit. However, such an invention has a limitation in that the height of the impeller is increased and the length of the main wing is made longer as the length of the main wing and the auxiliary wing are overlapped.

Korean Patent No. 10-1342746 discloses a conventional impeller in which a plurality of auxiliary blades are installed between a plurality of main blades to reduce the blade pitch to increase the aspect ratio. Such an impeller has a disadvantage in that the overlapping portion of the main wing is broken due to the difficulty of the injection mold, thereby reducing lift and increasing noise.

2, the wings and the flow angle of the backward-arc centrifugal impeller 20 are shown. The pressure rise of the impeller and the work by the Euler equation have the relationship as shown in the following equation (2).

Where η _R is the efficiency of the impeller as a percentage of the actual transfer energy excluding the flow losses at the theoretical rise in voltage due to the internal flow versus the theoretical transfer energy.

The flow from the impeller shown in Fig. 2 does not flow along the outlet wing and a slip occurs, and when the blade angle is? _2b , the slip coefficient is?

, And the slip coefficient ( _E ) is expressed by the following equation (3) using the Stodola equation.

Where N _B is the number of wings, β ₂ is the exit flow angle, and U ₂ and C _m2 are the radial components of the wing tip rotation velocity and the absolute velocity of the exit flow, respectively. From the equations (2) and (3), in order to increase the pressure transmission, it is necessary to increase the rotation component _Cθ2 of the absolute velocity of the exit, and to increase the slip coefficient by increasing the number of vanes possible.

US Patent Application US 2009/0155048 A1 discloses an example in which a split vane, which is an auxiliary wing that rotates coaxially with main wings in a centrifugal pump impeller, is installed between main wings to increase the number of wings. However, unlike a centrifugal pump that produces a large static pressure, in a fan or blower that requires an increase in flow rate rather than an increase in pressure, the height-to-diameter ratio of the impeller is much larger than the pump, so that the upper portion of the impeller blade is covered with a normal shroud plate, And the outlet had to be covered with a thin band-like disk to reinforce the strength. In this case, however, injection molding was difficult.

It is an object of the present invention to provide a method of installing a plurality of auxiliary blades rotating between axial blades and centrifugal impellers to reduce noise while reducing the height of the blades, In the centrifugal type, it is possible to reduce the flow separation of the negative pressure side, thereby improving the blade slip coefficient and reducing the flow separation noise by reducing the size of the wing wake flow. have.

According to an aspect of the present invention, there is provided a wireless communication device including a first portion having a first hub and a plurality of main blades extending at equal intervals along an outer periphery of the first hub; And a second portion having a plurality of auxiliary blades extending at an interval along an outer periphery of the second hub, wherein the second portion includes a first hub The projecting angle between LE and TE is Φ ₁ and the projection angle between the front and rear ends of the plurality of auxiliary blades is θ ₁ , And the angle Φ _1u , θ _1u, and the downstream angle Φ _1d , θ _1d, and Φ _1m , θ _1m in which each main wing and the auxiliary wing do not overlap, and φ ₁ and θ ₁ are the angles of the main wing and the auxiliary wing, From the hub to the end, 0 <θ ₁ < So as to satisfy the Φ _1, wherein θ ₁ is provided with an impeller which is smaller than the Φ _1.

The sizes of the first blades _{慮 1u} and 慮_1d may be angles that overlap the main blades so that the channel near the downstream side of the main blades is guided.

Wherein the first hub is formed with a plurality of first engaging projections spaced apart from each other on a bottom surface thereof and a plurality of first engaging grooves provided by the plurality of engaging projections, A plurality of second engagement grooves formed by the plurality of engagement protrusions are formed in the first engagement protrusions and the plurality of second engagement protrusions are coupled to the plurality of second engagement recesses, And may be coupled to the plurality of first coupling grooves.

The plurality of first engaging projections and the plurality of second engaging grooves are press-engaged and the plurality of second engaging projections are press-engaged with the plurality of first engaging grooves.

The plurality of first coupling protrusions may be adhesively coupled to the plurality of second coupling grooves by an adhesive, and the plurality of second coupling protrusions may be adhesively coupled to the plurality of first coupling grooves by an adhesive.

The first hub and the second hub may be formed in a strip shape.

The first and second hubs may have a single conical shape when coupled to each other.

According to another aspect of the present invention, there is provided a circular bottom plate, comprising: a circular bottom plate; a hub protruding from the center of the upper surface of the circular bottom plate; and a plurality of main blades circumferentially formed around the hub, part; And a second portion having a strip-shaped shroud and a plurality of auxiliary blades integrally formed at intervals along the bottom surface of the shroud, wherein an inlet area between the main vane negative pressure surface and the auxiliary vane pressure surface is defined as Ssu , The inlet area between the main wing pressure side and the auxiliary wing negative pressure surface is Spu and the area downstream of the negative pressure side channel of the main wing, which is the area downstream of each channel, is Ssd and the area downstream of the pressure side channel of the main wing is Spd The inlet angle of each auxiliary wing is the same as the angle of each main wing outlet, the inlet of the auxiliary wing is located at a position where an S-shaped curvature occurs, and the inlet angle of the auxiliary wing is equal to the flow angle tangent The above object can also be achieved by providing an impeller which is characterized in that the angle is an angle that makes it possible to achieve the above object.

The auxiliary blade front end (L.E.) may be located between the inlet and equal radius channels such that Ssu and Spu are the same.

The exit angle and the exit position between the channels can be set by rotating the auxiliary blade front end (T.E.) by rotating the auxiliary blade front end (L.E.) as a pivot point so that Ssu and Ssd are kept similar.

The shroud may have a strip shape.

The base plate has a plurality of first coupling grooves on the upper surface thereof for receiving the lower ends of the plurality of auxiliary blades, and a plurality of second coupling grooves for inserting the upper ends of the plurality of main blades are formed on the bottom surface of the shroud. have.

The lower ends of the plurality of auxiliary vanes may be pushed into the plurality of first coupling grooves and the lower ends of the plurality of main vanes may be pushed into the plurality of second coupling grooves.

The lower ends of the plurality of auxiliary wings are adhesively bonded to the plurality of first coupling grooves by an adhesive, and the lower ends of the plurality of main wings may be adhesively bonded to the plurality of second coupling grooves by an adhesive.

A plurality of auxiliary blades arranged one by one between the main blades can be arranged at different intervals along the rotational direction of the impeller.

The circular bottom plate and the shroud may be inclined in the downstream direction of the flow or parallel to the direction of the rotation axis.

The outer diameter of the circular bottom plate may be smaller than the inner diameter of the shroud.

The plurality of main blades and the plurality of auxiliary blades may be integrally coupled to the circular bottom plate and the shroud.

As described above, the impeller in which the auxiliary vanes are arranged in the channels between the main wings according to the present invention has the following advantages with respect to the axial flow type and the centrifugal type as described below.

In the case of the axial flow impeller according to the present invention, the secondary flow at the negative pressure side of the main blade can be reduced and the angle of departure at the rear end of the blade can be reduced to obtain pressure increase and noise reduction effect. In addition, when a plurality of auxiliary blades are arranged between a plurality of main blades so as not to increase the height of the impeller, a plurality of auxiliary blades, each of which includes a first part composed of an upper hub to which a plurality of main blades are connected, The upper hub and the lower hub are formed into a strip shape having a circumferential radial thickness so that the wings are overlapped in the injection molding process so that the upper and lower hubs Can fundamentally solve difficult problems.

In the case of the centrifugal impeller according to the present invention, the secondary flow at the negative pressure side of the hybrid S-type main wing combined with the backward wing and the forward wing or the radial is reduced and the increase of energy transfer and noise reduction Effect can be obtained. A second part made of a shroud having a plurality of auxiliary blades attached thereto is injection molded as a separate component, and a plurality of main blades are coupled to the shroud concavely and convexly So that the problem caused by the injection molding can be solved.

FIG. 1 is a view for explaining flow-related design variables and blade-related design parameters between general axial flow impeller blades.

2 is a view for explaining design variables related to a blade and a flow angle of a conventional backward centrifugal impeller.

3 is an assembled perspective view illustrating an axial flow impeller according to an embodiment of the present invention.

Fig. 4 is an exploded perspective view showing the bottom surface of the first portion of the axial-flow impeller shown in Fig. 3 and the top surface of the second portion at the same time.

FIG. 5 is a schematic view of a flow around a wing of an axial flow impeller according to an embodiment of the present invention and a conventional impeller together with a wired line.

6 is a view showing a structure between a main blade and an auxiliary blade of an axial flow impeller according to an embodiment of the present invention.

7 is an assembled perspective view illustrating a centrifugal impeller according to another embodiment of the present invention.

8 is an exploded perspective view showing the bottom surface of the first part of the centrifugal impeller shown in FIG. 7 and the top surface of the second part at the same time.

FIG. 9 is a view showing an example in which the flow shape of the main wing of the centrifugal impeller according to another embodiment of the present invention is a reverse wing (indicated by a solid line) and having an auxiliary wing in the form of a split vane, (Indicated by a dotted line).

10 is a cross-sectional view showing a main blade and an auxiliary blade of a centrifugal impeller according to another embodiment of the present invention.

11 is a view showing an example in which the positions of the channels of the auxiliary vanes of the centrifugal impeller according to another embodiment of the present invention are randomly arranged without being equally arranged in the rotating direction.

11 is a view showing an example in which the positions of the channels of the auxiliary vanes of the centrifugal impeller according to another embodiment of the present invention are randomly arranged without being equally arranged in the rotating direction.

12 is a perspective view showing an impeller having a main wing and a secondary wing according to another embodiment of the present invention.

13 is a plan view showing an impeller according to another embodiment of the present invention.

14 is a cross-sectional view taken along the line A-A shown in Fig.

[Description of reference numerals]

110: first part

111: First hub

115: first engaging projection

117: first coupling groove

120: Main wing

130: Second part

131: second hub

135: second engaging projection

137: second engaging groove

140: Auxiliary wing

Hereinafter, an axial flow type impeller according to an embodiment of the present invention and a centrifugal type impeller according to another embodiment will be sequentially described with reference to the drawings.

FIG. 3 is an assembled perspective view illustrating an axial flow impeller according to an embodiment of the present invention, and FIG. 4 is an exploded perspective view illustrating a bottom surface of the first portion of the axial flow impeller shown in FIG. 3 and an upper surface of the second portion at the same time .

Referring to FIG. 3, the axial flow impeller 100 according to an embodiment of the present invention includes a first part 110 and a second part 130 which are separate parts. The separately manufactured first part 110 and the second part 130 are used as an impeller in a mutually coupled state.

Referring to FIG. 4, the first portion 110 includes a first hub 111 having a substantially ring shape, a plurality of primary blades 120 (not shown) formed at equal intervals on the outer circumferential surface of the first hub 111, ).

The first hub 111 may be formed with a hole 113 at the center so as to be connected to a predetermined driving member such as a rotating shaft (not shown) for rotationally driving the axial flow impeller 100.

In addition, the first hub 111 has a plurality of first coupling protrusions 115 protruding at equal intervals along the bottom surface thereof. In this case, a plurality of first coupling grooves 117 into which a plurality of second coupling protrusions 135 to be described later are inserted are provided between the respective first coupling protrusions 115.

A plurality of main blades 120 are integrally connected to the outer circumferential surface of one end of the hub 111 and bent at a predetermined curvature toward the other end.

4, each main wing 120 includes a negative pressure surface 121, a pressure surface 123 located on the opposite side of the negative pressure surface, a wing hub surface 125 adjacent to the first hub 111, And a wing tip surface 127 at the end of the wing tip 120. In this case, the upper end of each main wing 120 is defined as a front end (L.E.) and the lower end is defined as a rear end (T.E.).

The second portion 130 includes a second hub 131 formed in a substantially ring shape and a plurality of primary blades 140 formed at equal intervals on the outer circumferential surface of the second hub 131.

Also, the second hub 131 may have a hole 133 formed at the center thereof, like the first hub 111. In this case, the outer diameter of the second hub 131 may be the same as the outer diameter of the first hub 111, and the inner diameter of the second hub 131 may be equal to or smaller than the inner diameter of the first hub 111 Which is a structure that can be considered for securing the impeller 100 to a rotating driving member corresponding to the rotating shaft or the rotating shaft.

In addition, the second hub 131 has a plurality of second coupling protrusions 135 formed at equal intervals along the upper surface thereof. In this case, a plurality of second coupling grooves 137 are formed between the second coupling protrusions 135, into which a plurality of first coupling protrusions 115 are inserted.

As described above, the first and second hubs 111 and 131 are configured such that a plurality of first coupling protrusions 115 are inserted into the plurality of second coupling grooves 137, and at the same time, a plurality of second coupling protrusions 135 And are coupled to each other as they are respectively inserted into the first coupling grooves 117 of the main body 110. [ In this case, the first and second hubs 111 and 131 may be coupled to each other in a compressed state or may be bonded to each other using a separate adhesive.

The plurality of auxiliary vanes 140 are integrally connected to the outer circumferential surface of the second hub 131 at one end and curved at a predetermined curvature toward the other end. In addition, when the first and second hubs 111 and 131 are coupled to each other, the plurality of auxiliary blades 140 may be disposed below the plurality of main blades 120, respectively.

4, each of the auxiliary vanes 140 includes a negative pressure surface 141, a pressure surface 143 located on the opposite side of the negative pressure surface, a vane hub surface 145 adjacent to the second hub 131, And a wing tip surface 147 at the end of the wing tip 140. In this case, each of the auxiliary vanes 140 defines the upper end thereof as a tip end (L.E.) and the lower end thereof as a rear end (T.E.).

FIG. 5 is a schematic view of a flow around a wing of an axial flow impeller according to an embodiment of the present invention and a conventional impeller together with a wired line.

Referring to FIG. 5A, when the inlet angle is + (that is, when the inlet flow is incident on the pressure surface side with respect to the inlet wing camber tangential direction), the flow separation on the negative pressure surface S due to the camber of the wing So that the streamline can not flow along the wing and deviate toward the negative pressure side than the tangential direction of the wing tail camber. In this case, the flow of the thick boundary layer due to the flow separation near the rear end of the wing proceeds and a thick wake flow of δ 'occurs. In FIG. 5 (a), reference numerals P denote the pressure surfaces of the vanes.

However, in the present invention, as shown in FIG. 5 (b), an auxiliary blade 140 is disposed between two main blades 120. Accordingly, unlike the inlet area A flow is decelerated from the entrance area A ₁ between 5 main blade as shown in (a) creating a channel flow of ₂ and A ₃ occurs the flow separation, in the inlet area A ₂ near rather accelerates The flow separation is eliminated at the downstream side of the negative pressure surface 121 of the main wing 120. In addition, due to the small amount of flow separation at the negative pressure surface 141 of the auxiliary vane 140, a narrow wake thickness? 'Is generated and the deviation angle? Between the channels is also reduced to cause an increase in pressure by the vane camber, A larger camber angle can be applied.

6 is a view showing a relationship between a main blade and an auxiliary blade of an axial flow impeller according to an embodiment of the present invention.

6, the first cylinder angle between the front end LE and the rear end TE of the main wing 120 is Φ ₁ and the front end LE and the rear end TE of the same number of the auxiliary wings 140, Lt; _{RTI ID = 0.0} &gt; _{1. &} Lt; / _RTI &gt;

The first cylinder head angle? ₁ is composed of an upstream angle? _1u overlapping with the auxiliary vane 140, a downstream angle? _1d, and? _1m which does not overlap with the auxiliary vane 140. Here, Φ _{1u =} θ _1d , Φ _{1d =} θ _1u , and these values change as the blade radius goes from the hub to the end. If? ₁ =? _1, then the number of the same blades would be doubled, so that the present invention is 0 <? ₁ < ₃ and the rear end of the auxiliary wing 140 coincides with the rear end of the main wing 120 so that the impeller 100 (see Fig. 3) not to increase the height of and (see 121, Fig. 4) the suction side of the auxiliary wings of the cursor θ _1u main blade 120 than θ _1d so that the vicinity of the downstream guide channel fully.

As described above, the first hub 111 and the second hub 131 are formed by the first and second coupling protrusions 115 and 135 and the first and second coupling grooves 117 and 137 as shown in FIG. 3 They are mutually coupled. The rear end portion of the main wing 120 corresponding to the downstream angle Φ _1d of the main wing 120 is not attached to the first hub 111 but is tightly coupled to the second hub 131.

Although not shown in the drawing, the first and second hubs 111 and 131 may be formed in a conical shape instead of a cylindrical shape. For example, when the second hub 131 is coupled to the lower side of the first hub 111, a single conical shape may be formed as a whole. If the first and second hubs are formed in the shape of a cone, they can also be used as a saddle type impeller.

FIG. 7 is an assembled perspective view illustrating a centrifugal impeller according to another embodiment of the present invention, and FIG. 8 is an exploded perspective view illustrating a bottom surface of the first part of the centrifugal impeller shown in FIG. 7 and an upper surface of the second part at the same time .

Referring to FIG. 7, the centrifugal impeller 200 according to another embodiment of the present invention, like the axial flow impeller 100 according to the above-described embodiment of the present invention, 1 &lt; / RTI &gt; portion 210 and a second portion &lt; RTI ID = 0.0 &gt; 230 &lt; / RTI & The first portion 210 and the second portion 230 are used as an impeller in a state of mutual engagement.

Referring to FIG. 8, the first portion 210 includes a hub 211, a base plate 225 formed of a circular plate, and a plurality of main blades 220 formed at regular intervals.

The hub 211 may be formed with a hole 213 at the center so as to be connected to a predetermined driving member such as a rotating shaft (not shown) for rotating the centrifugal impeller 200. The hub 211 may have a substantially conical shape.

The lower plate 215 is integrally formed with the lower end of the hub 211 integrally formed at the center of the upper surface. A plurality of main blades 220 are arranged at equal intervals along the circumferential direction of the base plate 215 and the lower ends of the plurality of main blades 220 are integrally connected to the upper surface of the base plate 215.

The base plate 215 is formed with a plurality of first coupling grooves 217 between which the lower ends of a plurality of auxiliary vanes 240 described later are inserted between the main blades 220 adjacent to each other on the upper surface.

A plurality of main blades 220 are arranged such that a front end (L.E.) is disposed adjacent to the outer circumferential surface of the first hub 211 and is bent at a predetermined curvature from the front end to the rear end (T.E.).

Each main wing 220 has a negative pressure surface 221, a pressure surface 223 located on the opposite side of the negative pressure surface, a wing undersurface 225 adjacent to the bottom plate 215 and a shroud And a wing top surface (227) adjacent to the wing surface (231). In this case, the inner end of each main wing 220 is defined as a front end (L.E.), and the outer end is defined as a rear end (T.E.).

The second portion 230 includes a shroud 231 having a generally ring shape and a plurality of auxiliary blades 240 formed at equal intervals along the bottom surface of the shroud 231. In this case, the plurality of auxiliary blades 240 may be formed in an arc shape or an S shape.

The outer diameter of the shroud 231 may be approximately the same as the outer diameter of the bottom plate 215. A plurality of second coupling grooves 233 are formed in the bottom surface of the shroud 231 to insert a plurality of main blades 220 between the plurality of auxiliary blades 240. And a plurality of upper ends of the plurality of main blades 220 may be respectively inserted into the plurality of second coupling grooves 233.

As the lower ends of the plurality of auxiliary vanes 240 are inserted into the plurality of first coupling grooves 217 and the upper ends of the plurality of main vanes 220 are inserted into the plurality of second coupling grooves 233, And the first and second portions 210 and 230 are coupled to each other. In this case, each of the engaging portions may be bonded to each other in a state of being pressed together or may be bonded to each other by using a separate adhesive.

The plurality of auxiliary vanes 240 each include a negative pressure surface 241 and a pressure surface 243 located on the opposite side of the negative pressure surface and a wing lower surface 245 and a wing top surface 247 adjacent to the shroud 231 . In this case, the inner end of each auxiliary wing 240 is defined as a tip end (L.E.), and the outer end is defined as a rear end (T.E.).

FIG. 9 is a view showing an example in which the flow shape of the main wing of the centrifugal impeller according to another embodiment of the present invention is a reverse wing (indicated by a solid line) and having an auxiliary wing in the form of a split vane, FIG. 10 is a cross-sectional view showing a main blade and an auxiliary blade of a centrifugal impeller according to another embodiment of the present invention. FIG.

Referring to FIG. 9, a dotted line indicates that the flow shape of the main wing of the centrifugal impeller is indicated by a solid line, and a dotted line indicates that the wake flow shape of the centrifugal impeller is the forward flow.

In this case, there is a wake flow between the blades due to the slip, except for the pressure surface, as indicated by the blue solid line in the backward curved shape which is bent in the opposite direction to the rotational direction. On the other hand, the energy loss of the wake is larger than that of the backward wing exit wing because the flow wing is bent in the rotational direction like the orange solid line in the forward wing where the main wing outlet is bent in the same direction as the rotation direction. However, the increase in the pressure energy due to the increase of C? ₂ in Equation (2) is relatively large at the rotational direction outlet relative speed.

In order to simultaneously utilize the high efficiency of the rearward wing and the high pressure energy of the forward wing blade, the hybrid wing of the S shape is shown in FIG. 10, but in order to overcome the large flow separation of the forward wing- The auxiliary wing, called the split vane, is installed between the main wings. By dividing the channel into two as in the axial flow type impeller, the slip and wake flow on the main wing negative pressure side are reduced like the green solid line, Since there is a wake flow with flow separation, it is most preferable among the three flow types.

In FIG. 9, reference numerals U ₂ and C _m2 denote radial components of the blade tip rotational speed and the absolute velocity of the exit flow, respectively, C _θ2 is the rotational component of the exit absolute velocity, C ₂ and W ₂ are the exit absolute velocity The magnitude of the vector and the magnitude of the exit relative velocity vector.

10, the channel in the hybrid wing for providing the auxiliary wing has an inlet area Ssu between the main wing negative pressure face and the auxiliary wing pressure face, where u is an index indicative of the upstream side, between the main wing pressure face and the auxiliary wing negative pressure face The inlet area Spu of each channel, and the area Ssd and Spd downstream of each channel. Generally, the height of the vane inlet is almost the same as the height of the outlet. Therefore, And flow separation due to pressure increase.

In the present invention, the outlet angle of the auxiliary vanes is kept close to the main vane outlet angle (β _{2b in} FIG. 2) so that the inlet area Ssu and the outlet area Ssd of the main vane negative pressure side channel do not greatly vary, And the inlet angle of the auxiliary vane is such that the flow angle tangent coincides with the main stream line between the channels. In addition, even if the auxiliary wing is placed at the center of the two main wings, the auxiliary wing shear (LE) is moved between the same radius channels so that Ssu is smaller than Spu, so that the two areas are equal. The position of the outlet between the exit angle and the channel can be determined by moving the auxiliary blade front end (LE) at the obtained position to the pivot point and the auxiliary blade rear end (TE) between the outlet and the same radius channel.

11 is a view showing an example in which the positions of the channels of the auxiliary vanes of the centrifugal impeller according to another embodiment of the present invention are randomly arranged without being equally arranged in the rotating direction.

The position of the auxiliary vanes of the centrifugal impeller is not randomly arranged in the direction of rotation but is randomly arranged as shown in Fig. 11, and the flow separation vortex and the channel passing vortex In this case, it is possible to arrange the thrust and thrust balance by an axial vertical surface by the lift distribution.

Meanwhile, the centrifugal impeller 200 shown in FIG. 7 is a type of impeller coupling the first part 210 and the second part 230, and the first and second parts 210 and 230 are separately manufactured. However, the present invention is not limited to this, and an impeller constituting a single body can be provided. A detailed description will be given with reference to Figs. 12 to 14. Fig.

FIG. 12 is a perspective view showing an impeller having a main wing and a secondary wing according to still another embodiment of the present invention, FIG. 13 is a plan view showing an impeller according to another embodiment of the present invention, and FIG. 13 is a cross-sectional view along the line AA shown in Fig.

12 to 14, the outer diameter of the circular bottom plate 315 may be formed to be slightly smaller than the inner diameter of the shroud 331 in order to inject the impeller 300 into a single body according to another embodiment of the present invention .

In this case, the circular bottom plate 315 and the shroud 331 are all inclined in the flow downstream direction as shown in FIG. 14, but they are not limited thereto and may be formed in a horizontal direction so as to be perpendicular to the direction of the rotation axis.

The plurality of main blades 320 and the plurality of auxiliary blades 330 provided on the impeller 300 are integrally formed with the shroud 331 and the circular bottom plate 315 or the hub 317 Can be combined. That is, the plurality of main blades 320 are connected to the shroud 331 at the upper end and connected to the circular bottom plate 315 or the hub 317 at the lower end. Also, a plurality of auxiliary vanes 330 are connected to the shroud 331 at the upper end and connected to the circular bottom plate 315 or the hub 317 at the lower end.

In this case, the plurality of main blades 320 and the plurality of auxiliary blades 330 may be formed alternately along the circumferential direction.

On the other hand, the axial flow impeller 200 shown in FIG. 7 is discharged after the flow is introduced in the direction of the rotation axis, and then the pressure is raised in the radial direction perpendicular to the direction of the rotation axis. In the alternative impeller 300 shown in FIG. 12, the flow is introduced in the direction of the rotation axis, and the pressure is increased with a predetermined inclination relative to the direction of the rotation axis similarly to the axial flow type. In this case, the flow-type impeller 300 may have the same flow path as the flow direction of the wire shown in FIG.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit and scope of the invention. It is therefore intended that such variations and modifications fall within the scope of the appended claims.

Claims (18)

1. A first portion having a first hub and a plurality of main blades extending equidistantly along an outer periphery of the first hub; And

   And a second portion having a second hub that is concavo-convex coupled to the lower side of the first hub and a plurality of auxiliary wings extending at an interval along the outer circumference of the second hub,

   When the projection angle between the front end LE and the rear end TE of each main wing is Φ ₁ and the projection angle between the front end LE and the rear end TE of a plurality of auxiliary wings is θ ₁ ,

   Is composed of the respective main wing and the auxiliary wing overlapping the upstream angle Φ _1u, θ _1u and a downstream angle Φ _{1d, 1d} and θ, Φ _{1m, 1m} θ do not overlap each main wing and the auxiliary wing,

   The Φ ₁ and θ ₁ is the radius of the main blade and the auxiliary blade going from the end of each hub 0 <θ ₁ < So as to satisfy the Φ _1, the impeller ₁ is θ which is smaller than the Φ _1.
2. The method according to claim 1,

   And the magnitudes of? _1u and? _1d of the auxiliary vanes are angles that overlap with the main vane so that a channel near the downstream of the main vane negative pressure surface is guided.
3. The method according to claim 1,

   Wherein the first hub has a plurality of first coupling protrusions spaced apart from each other on a bottom surface thereof and a plurality of first coupling grooves formed by the plurality of coupling protrusions,

   Wherein the second hub has a plurality of second coupling projections spaced apart from each other on an upper surface thereof and a plurality of second coupling grooves formed by the plurality of coupling projections,

   Wherein the plurality of first engaging projections are engaged with the plurality of second engaging grooves,

   And the plurality of second engaging projections are coupled to the plurality of first engaging grooves.
4. The method of claim 3,

   A plurality of first engaging projections and a plurality of second engaging grooves,

   And the plurality of second engaging projections are press-engaged with the plurality of first engaging grooves.
5. The method of claim 3,

   Wherein the plurality of first engaging projections are adhesively bonded to the plurality of second engaging grooves by an adhesive,

   Wherein the plurality of second engaging projections are adhesively joined to the plurality of first engaging grooves by an adhesive.
6. The method according to claim 1,

   Characterized in that the first hub and the second hub are in the form of strips
7. The method according to claim 1,

   Wherein the first and second hubs are of a single conical shape when coupled to each other.
8. A first portion having a circular bottom plate, a hub protruding from the center of the upper surface of the circular bottom plate, and a plurality of main blades circumferentially formed around the hub at equal intervals on an upper surface of the circular bottom plate; And

   And a second portion having a strip-shaped shroud and a plurality of auxiliary blades integrally formed at intervals along the bottom surface of the shroud,

   The inlet area between the main wing pressure side and the auxiliary wing pressure face is Ssu and the inlet area between the main wing pressure face and the auxiliary wing negative pressure face is Spu and the area of the main wing downstream of each channel If the area is Ssd and the downstream area of the pressure side channel of the main wing is Spd,

   The exit angle of each auxiliary wing is the same as the angle of each main wing exit,

   The inlet of the auxiliary vane is located at a position where an S-

   Wherein the inlet angle of the auxiliary vane is an angle that the flow angle tangent line coincides with the main flow line of the channel.
9. 9. The method of claim 8,

   Wherein the auxiliary blade front end (L.E.) is located between the inlet same radius channels such that Ssu and Spu are the same.
10. 9. The method of claim 8,

    (TE) is rotationally moved between the same radial channels of the outlet with the auxiliary blade front (LE) as a pivot point so that the Ssu and the Ssd are kept similar to each other, thereby setting the outlet angle and the outlet position between the channels Impeller.
11. 9. The method of claim 8,

    Wherein the shroud is in the shape of a strip.
12. 9. The method of claim 8,

    Wherein the bottom plate has a plurality of first coupling grooves formed on an upper surface thereof to receive the lower ends of the plurality of auxiliary blades,

    Wherein the shroud has a plurality of second coupling grooves formed in its bottom surface to receive the upper ends of the plurality of main blades.
13. 13. The method of claim 12,

    A lower end of the plurality of auxiliary vanes is press-coupled to the plurality of first coupling grooves,

    And the lower ends of the plurality of main blades are press-coupled to the plurality of second coupling grooves.
14. 13. The method of claim 12,

    Wherein the lower ends of the plurality of auxiliary vanes are adhesively bonded to the plurality of first coupling grooves by an adhesive,

    And the lower ends of the plurality of main blades are adhesively joined to the plurality of second coupling grooves by an adhesive.
15. The method according to claim 1 or 8,

    And a plurality of auxiliary blades arranged one by one between the main blades are arranged at different intervals along the rotational direction of the impeller.
16. 9. The method of claim 8,

    Wherein the circular bottom plate and the shroud are inclined or horizontally oriented in a downstream direction of flow.
17. 17. The method of claim 16,

    Wherein an outer diameter of the circular bottom plate is smaller than an inner diameter of the shroud.
18. 17. The method of claim 16,

    Wherein the plurality of main blades and the plurality of auxiliary blades are integrally coupled to the circular bottom plate and the shroud.

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