FI99159C - Supply air device and method for adjusting the supply air device - Google Patents

Description

99159

Supply air device and method for adjusting the intake air device Anordning för ingangsuft och förfarande förbleg av en anordning förganggangt 5

The invention relates to a supply air device and a method for controlling a supply air device.

DE patent 3 410 078 discloses a supply air device solution in which the apparatus comprises fixed circumferentially arranged wings which are attached to a central core tube 10. In the device solution, the air flow through the device is controlled by moving the valve plate at the end of the core tube simultaneously with the second controller. The second regulator consists of a locking ring. Thus, in the solution according to DE 3 410 078, the position of the first and second controllers is adjusted simultaneously.

15 This application presents a much simpler solution than that used in the structure of the DE solution. The invention has realized the use of only a sealing ring and a vane structure in which the vane structure is selected so as to obtain a sufficient deflection of air to the side without the need for a separate core tube and an associated valve plate closing and opening said tube.

20

In the solution according to our invention, the air flow is derived with small amounts of air flow '. two roads; the first path as a flow L1 through the vanes and the second path L2 as a side flow, whereby the side flow directs the total flow downwards and prevents the turbulent flow through the vanes from spreading to the side. The side flow then acts as a kind of • · • «· · 25 curtain shower. When the side flow path is closed in the structure according to our invention »· by means of the wings only, the air flow is deflected to the side so that the air flow; *; travels along the curved surface of the outer tube and under the influence of the Coanda effect-. · · Attached, resulting in a wide total airflow pattern.

»1

According to the invention, a wing structure is used which comprises at least two wing circumferences. Due to the above-mentioned advantageous structure, the device does not require a central I "control part for a separate central flow, as is the case, for example, in the structure according to DE patent 2 99159 3 410 078. The at least two-circumferential structure according to our invention is particularly advantageous in control situations. This is not achieved by the prior art solution only by means of the vanes, but the above-mentioned lateral deflection is realized by means of a separate guide plate adapted to adjust a separate average flow.

Our application further discloses a preferred embodiment of the invention, in which the position of the shut-off ring is automatically adjusted when adjusting the amount of air flow through the valve. The higher the pressure applied to the sealing ring of the supply air device, the greater the force 10 is pressed against it and the associated sealing ring against the spring force, and thus the sealing ring and the associated seal or the like are moved forward. Even in the second extreme position of the closure, the air flow path of the inlet end of the impeller tube is closed to the side flow and the air flow is directed through the impeller tube to the vanes which deflect the flow downwards and to the side. Thus, the solution adjusts the airflow throw pattern according to the airflow amount. The larger the amount of air, the more air flow is applied by reducing the side flow through the annular flow paths between the outer tube and the impeller tube.

The supply air device according to the invention is characterized in that in the supply air device structure 20 the impeller has at least two circumferences, thus comprising a first impeller tube and; between the central axis of the wings and that there is at least a second wing ring comprising wings arranged between the wing tube and the wing tube.

I $ * r 9 · • ·

• I

The method according to the invention is characterized in that the method flows into the air through at least a double-circumferential wing structure.

The invention will now be described with reference to some preferred embodiments of the invention shown in the figures of the accompanying drawings, for which the invention is not intended. ‘’. however, exclusively restrict.

30 «·

»· I

t · ♦ l · · • 99159 3

Figure 1A shows an axonometric supply air device according to the invention.

Fig. 1B shows the supply air device according to Fig. 1A, in which the movable closing part can be set to different closing positions by turning the end plate O on the inner spindle 5 to which the closing part is connected. The figure shows the supply air device in a position allowing side flow.

Fig. 1C shows the closing part of the supply air device of Fig. IB in the closing position of the side flow paths.

10

Figure 2A shows a second embodiment of the invention in a cross-sectional view. Figure 2A shows the first adjustment position of the device according to the invention. The actuator for moving the closing part is a pneumatic cylinder.

Fig. 2B shows a second adjustment position of the device according to Fig. 2A, in which the side current path is closed.

Figure 2C shows an embodiment of the invention in which an electric motor is used as the actuator for moving the closing part.

20,; In Figure 2D is shown in Figure 2A, the supply air device as seen from the direction of arrow K f · ·, puolileikkauksena.

i i · «9 9 · 9 9 • '# 9; Figure 3A shows an axonometric view of the attachment of the wing to the impeller tube and the central shaft.

• · • · $ 9 I ·! t Figure 3B shows an impeller consisting of two groups of vanes.

Figures 4A and 4B show an embodiment enabling automatic operation, a spring construction in which the closure member is movable against a spring force to automatically adjust the side flow depending on the amount of air flow and / or the pressure applied to the closure member. Fig. 4A shows the second extreme position of the closing part, in which the air flow through the side flow paths is at its maximum. Figure 4B shows the closure part in the position in which the side flow path is closed.

Figure 1A shows an axonometric view of a supply air device according to the invention. The supply air device 10 comprises an outer tube 11 which terminates in a curved collar 12. Inside the structure there is a wing circumferential tube 13 and is associated with radially arranged fixed non-rotating blades 14a'j, 14a'2 ... The wings 14a !, 14a2 ... are connected at their bases to a fixed flow-impermeable central shaft 15 and at its outer ends to the impeller tube 13 '.

10 The wings Ua’j.MaV .. are connected at their bases to the impeller tube 13 ’.

The central shaft 15 comprises an outer telescopic body 15aj which is in a fixed position and an inner second body 15a2 movable relative thereto. Frames 15a! and 15a2 there is a spring J. The body 15aj is further associated with a central mandrel 15a3, which comprises at its end a rotating plate O. The mandrel 15a3 comprises threads C2 on its outer surface and respectively a telescopic body 15a2 comprises a through hole G for the mandrel 15a3 and threads Cj. Thus, by rotating the mandrel 15a3 from the end piece O, the telescopic body 15a2 and the associated closure portion 16 comprising the sealing ring 16b are moved. or the like. Thus, by manually moving the closing part, the annular flow path F between the impeller tube 13 and the outer tube 11 is opened and closed.

The embodiment of Figure 1A has two wings, wings Dj and D2. The inner wing: Dj comprises a smaller number of wings 14a !, 14a2 ... than the outer wing: D2, where the number of wings 14a '^ MaV .. is larger, preferably twice as large as in the inner wing Dj.

Fig. 1B shows a cross-sectional view of a supply air device according to the invention.

•: "* In the embodiment of the figure, there is a separate closure part 16 which is connected to the movement of the central shaft 15 but to the body part 15a2. The body part 15a2 is located inside the fixed body part 15aj and is movable with respect to said fixed body part 15aj. Between 15a2 there is a spring J. The mandrel 15a3 is introduced into the shaft 15 centrally and comprises at its end a plate 0 99159 from which the mandrel 15a3 can be rotated.The outer surface of the mandrel 15a3 has threads C2 cooperating with the threaded opening Cj of the end opening G G may also comprise a metal sleeve with threads, thus manually rotating the mandrel 15a3 from outside the actuator moves the portion 15a2 and the associated closure portion 16 and thereby controls the closing and opening of the side flow paths F. The shaft 15 preferably consists of four portions. a structure within which movement is arranged telescopically ground body 15a2. Part 15a2 is also preferably plastic. The mandrel 15a3 is preferably a threaded rod and is adapted to be rotatable in the threads C1 of the portion 15a2 (preferably such that a threaded sleeve (not shown) is fitted to the portion 15a2. The outer surface of the portion 15a3 preferably has a metal tube 15a'j to which the wings are welded. The material of the tea, such as the material of the wings, is generally metal, but other materials may be used.

Fig. 1B shows the side flow path F in the open position and Fig. 1C shows the control position of the supply air device in which the side flow path F is closed. When the side flow path F is in the open position, the flow through the side flow paths F is allowed and this side flow acts as a curtain jet and thus also directs the flow Lj directly downwards.

. . *. When the side flow path F is closed, the flow is distributed by means of a double-circumferential wing structure • j · 20 preferably also efficiently to the side in the room H.

Figure 2A shows a second embodiment of the invention in a cross-sectional view.

::: Figure 2A shows the air side flow L? permissive position. According to the invention, the closing part 16 and its sealing ring 16b or the like are moved by an actuator 17. 1 2 3 4 5 6

The central axis 15 is a flow-impermeable structural part comprising a telescopic frame structure having a first telescopic frame 15aj and a second frame 15a2 movable relative thereto 3 • · · v * movable relative thereto. In addition, a central spindle 15a3 is connected to the first body 15aj, comprising a piston 15a4 at the end 5. The part 15aj may further comprise a surrounding metal outer tube 6 15a 'j into which the vanes are welded at their bases. The actuator 17 is preferably a pneumatic cylinder with a fixed an overpressure is generated in the pressure space M 99159 6 between the piston 15a4 and the cylinder body 15b and the linearly movable telescopic inner body 15a2 and the associated closure portion 16 and its sealing ring 16b or the like are moved from the piston rod 15a3 towards the vanes 14 and The spring J is located between the parts 5 1582 and 15a2. The spring J returns the closing part 16 to its original position when no more pressure is applied to the space M.

Fig. 2A shows the adjustment position of the device, in which the air flow is controlled (arrow L1) both through the vanes 14a1, 14a2 ...; 14a'i, 14a'2 ... and between the impeller tube 13 and the outer tube 1110. The air flow through the wings, i.e. between the wing tubes 13,13 'and the wing tube 13' and the central shaft 15, is indicated centrally by the arrow Lj and the air flow between the wing tube 13 and the outer tube 11 is indicated by the arrow L ?. The flow is directed directly downwards and acts as a ring-shaped curtain shower, known per se.

As shown in Fig. 2A, the inner telescopic body 15a9 is connected by its flange 15as to the closing part 16, i.e. the closing ring. Using the actuator 17, the ring 16 is moved in the direction shown by the arrow Sj in Fig. 2A. When the closing part 16 is in the position shown in Fig. 2A, the flow through the vanes is allowed, i.e. between the wing circumferential tubes 13 and 13 'and the wing circumferential. between the tube 13 and the central shaft 15 and through the flow path F 20 between the impeller tube 13 and the outer tube 11. The air flow through the vanes 14aj, 14a2 is shown by the arrows Lj and

IMI

flow through the annular flow paths F between the impeller tube 13 and the outer tube 11: ‘: is shown by the arrows L · ,.

• · · ^ - • · • «·

• I I

• · · · • · f V · Figure 2B shows the position of the sealing ring 16 in which flow is allowed only 1 2 3 4 5 6

II

through the centrally, i.e. radially, wings 14a1,14a2 ... of the impeller tube 13 • · 2: (flow arrows Lj).

3 I 1 «4

• · · t · I

5

The adjustment position shown in Fig. 2B is particularly suitable for large air volumes, in which case it is desired to produce a large amount of air in the room H. With large air volumes 6 the airflow closes access to the annular duct F between the impeller tube 13 and the outer tube 11 by moving the closing ring 16 in the direction indicated by the arrow Sj. comes against the end N of the impeller tube 13. In this case, an air flow is applied. There is then no flow L2, so the so-called the curtain jet operation is inhibited and the wings Dj ^ ... of the impeller 143 ^ 1432 - .. 5143 ^, 143 ^ ... effectively distribute the flow to the side.

5

Figure 2C shows an embodiment of the device according to the invention, in which the actuator 17 moving the locking ring 16 is an electric motor. As shown in the figure, the structure is very similar to the pneumatic cylinder structure. The body 17a of the actuator 17 is fixedly connected to the closing part 16. In this embodiment, the mandrel 15a3 is a fixed part of the central shaft 15. Associated with the mandrel 15 is a rack 170 to which the gear shaft 172 of the output shaft of the electric motor 171 of the actuator 17 is operatively connected. When the control current is applied to the motor 171 attached to the body 17a, the rotational movement of both the shaft of the motor 171 and the gear 172 is converted into a linear movement of the body 17a. When no current is supplied to the electric motor, the spring J returns the closing part 16 to its initial position, where the flow path F to the side current 15 is open.

In Figure 2D is shown in Figure 2A and 2B, the structure of Figure 2A puolileikkauksena arrow K direction.

.: · 20 In the embodiments of the figures, there are preferably two wing frames. It is clear that as the supply air law increases, there may also be more wing frames.

• · • · • · ·: Figure 3A shows the wing structure axonometric in a partial view. The wing 14aj is: J 'welded to the central shaft 15 and to the inner circumferential wing tube 13' to its inner surface. The wing 14a'j is welded to the wing tube 13 'at its base and to the wing tube * * ·, · · 13 at its end.

• · · • · · 1 t «»

Fig. 3B shows an embodiment in which the wing structure comprises two wing groups, i.e. a first wing circumference Dj comprising wings 143-1432.1483 ... and a second wing 30 D2 comprising wings 14a'i, 14a'2.14a'3 ... Inner circumference D1 wing group 14aj, 14a2 ·. · Comprises about half as many wings as the outer circumference D2. The wing blades 14a1, 14a2 ... are connected at their base to the shaft 15 and at their ends to the wing tube 13 ', which is a tubular component. The wings 14a'j, 14a'2 ... of the impeller D2 are connected at their base to the impeller tube 13 'to its outer edge f, preferably by welding, and at their ends to the outer impeller tube 13. The impeller tubes 13,13' are circular cross-section tubes 5 with a wall thickness X10 of preferably 0.5 -2.0 mm and the length X20 in the flow direction is preferably in the range of 20-100 mm. The air flow direction is marked with Ljt.

The inner circumference Dj has a smaller number of wings than the outer circumference D2. Preferably, the outer circumference D2 has twice the number of wings relative to the inner circumference Dj. Each wing 14aj, 14a2 ...; 14a’j, 14a’2 ... has a constant radius (R) over the entire length of the wing. The tangent of the surface drawn to a certain point on the surface of the radius of curvature of the wing 14aj, 14a2 ...; 14a'j, 14a'2 ... and the central axis (X-axis) of the actuator drawn at said point and the central axis (X-axis) of the axis 15 the angle (α) between the lines is preferably in the range 10 ° <a <60 °. However, in each wing, the angle α is most preferably constant over the entire length of the wing. Likewise, in the same wing, the same α-angle and radius R are most preferably used in all the wings of both the wings of the circumference D1 and the wings of the circumference D2. The radius of curvature R has,,, the center of curvature Q and on each wing surface the centers of curvature Q form the center of curvature X '. In Fig. 3B, the X-axis line drawn at point P is denoted by v, and the tangent marked at point P is denoted by t, which tangent is perpendicular. ***: thus against the radius R. The center of curvature of the radius R is Q and is perpendicular to the center of curvature X '. Correspondingly, the ratio of the width h of the airflow-guiding surface of the wings 14aj, 14a2 ...; 14a'j, 14a'2 ... to the distance b of the wings at said wing length-25 is less than 0.5 over the entire length of the wing. The width h | t {I of the wing surface means the length of the wing lateral line, i.e. its so-called a circumferential dimension measured at the circumference of the V wing and in a plane perpendicular to the length of the wing. Wing length means measuring from the base of the wing to the tip of the wing. On each wing 14aj, 14a2 ...; 14a’j, 14a’2 ... is also a constant radius of curvature (R) along the entire length of the wing, which is in the region 30 <R <150 mm, but still substantially constant in the same wing.

I I '

I I

9 99159

The multi-circumferential vane structure shown in Fig. 3B is structurally simple and thus also enables the advantageous construction of larger diameter vane sizes.

Figures 4A and 4B show an embodiment of the invention in which the closing part 16 is moved 5 against the spring force of the spring J only by means of the air flow. The higher the air flow and / or its pressure, the greater the force applied to the closing part 16 and moving it and the seal 16b therein or the corresponding end N of the impeller tube 13 towards it. In its extreme position, the closing part 16, i.e. the closing ring, closes the annular side flow path F between the outer tube Ilja and the impeller tube 13. In this case, the side flow does not act as a jet of the ver-10, but all the flow passes through the vanes 14a1,14a2 ...; not only down so they also allow wide to the side. For small air flows, the side flow path F is completely open at its upper end, whereby by means of the side flow, when the side flow Lj acts as a curtain jet, the air flow L1 is effectively directed downwards. Also in this embodiment, the central shaft 15 is a telescopic structure-part 15 comprising an outer shaft part 15aj and an inner shaft part 15a2 moving relative thereto. The spring J is arranged inside the shaft part 15a2 to act on the end of the part 15a2 and on the inner end surface of the shaft part 15aj. Thus, the spring J is arranged between the shaft parts 15aj and 15a2 moving relative to each other. Shaft 15a2. is further connected, as in the previous embodiment, the closure portion 16 and the associated sealing ring 16b or the like. When the air flow affects the closing part 16 and the shaft 15a2

I I I I

to the end plate 15a5, the shaft 15a2 and the associated closure portion 16 are moved by the air flow against the spring force of the spring J and the closure portion 16 is moved to another extreme adjustment position where the closure portion 16, its sealing ring or the like 16b closes the side flow paths «K *. 15a3 in this embodiment acts only as a controller. Thus, the mandrel does not comprise threads in this embodiment.

• · »i t • · · ·» «· · · * •« * m · · »ψ I t«

Claims (16)

10 99159 A supply air device (10) comprising an outer tube (11) and at least one inner wing tube (13) and inside the wing tube (13) with wings (14aj, 14a2 - ..; 5 14a’j, 14a’2 ··). connected to the central axis (15) of the device at its base and end to the impeller tube (13, 13 '), characterized in that in the supply air device structure the impeller has at least two circumferences (Dj, Ö2) thus comprising vanes between the first impeller tube (13') and the central axis (15) 14aj, 14a2 · ..) and that there is at least a second wing ring (D2) comprising wings (Ua'j.Ha ^ ...) arranged between the wing ring tube (13 ') and the wing-10 tube tube (13). Supply air device according to Claim 1, characterized in that the inner circumference (Dj) has a smaller number of wings than the outer circumference (D2). Supply air device according to one of the preceding claims, characterized in that the wings (14aj, 14a2 ...; 14a'j, 14a'2) of the same impeller (Dj, Ö2) have a constant radius (R) which is preferably in the range 30 mm <R <150 mm and that the tangent (s) plotted at a certain point (P) on the surface of the wing and plotted in the plane of the radius of curvature (R) and. . the angle (a) between the axis (15) drawn at said point (P) and the line (v) parallel to the central axis (X- • · * V 20 axis) of the supply air device (10) is preferably in the range 10 ° <a <60 °, ·. : and that this angle (a) is, however, substantially constant in the same wing and that the wing • «. ···. (14aj, 14a2-.) The ratio of the width (h) of the airflow-guiding surface to the distance between the wings (b) is • · ·: less than 0.5 over the entire length of the wing. • · · · • · «• · · at Supply air device according to one of the preceding claims, characterized in that each wing (14aj, 14a2 to ..; 14a 'j, 14a'2) has a constant radius (R) of curvature over the entire length of the wing. Supply air device according to Claim 1, characterized in that the supply air device 30 (10) comprises an outer tube (11) and at least one wing (14aj, 14a2 *) inside the wing tube (13) and the wing ring, which are connected to a central shaft (15), in which the supply air device 11 99159 the structure has a first flow path for flow (Lj) through the vanes (14aj, 14a2 · ..; 14a'i, 14a'2 · ..) and a second flow path (F) through the annular channel between the wing circumferential tube (13) and the outer tube (11), wherein said flow (Ι ^>) through the side flow paths (F) is controlled by a separate shut-off part (16), and that the structure comprises a spring (J) against which the shut-off part (16) is movable against the spring force. Supply air device according to claim 1, characterized in that the closing part (16) is connected to the central shaft (15) by its movable shaft part (15a2) adapted to act by a spring (J), the spring (J) being located on the movable shaft part 10 (15a2) of the central shaft (15). ) and between the fixed shaft part (15a ^). Supply air device according to Claim 1, characterized in that the closing part (16) is connected to the actuator (17), the actuating means moving the closing part (16). Supply air device according to the preceding claim, characterized in that the actuator (17) is a cylinder device, preferably a pneumatic cylinder. Supply air device according to one of the preceding claims 8 or 9, characterized in that the cylinder device comprises a spindle (15a3) in a fixed position 20 relative to the central shaft (15). I · ·. ···. Supply air device according to the preceding claim, characterized in that • · • · ·:. the end of the spindle (15a3) is associated with a piston (15a4), whereby applying pressure to the pressure space (M) between the piston (15a4) and the cylinder body, the cylinder body and its associated closing part (16) are moved, preferably the sealing ring at the leading edge (N) ). Supply air device according to one of the preceding claims 1 to 7 or 9, characterized in that the actuator (17) for moving the closing part of the supply air device is a v. Electric motor. ,: 30 12 99159 Supply air device according to one of the preceding claims, characterized in that a spring (J) is arranged between the actuator (17) and the shaft (15), by means of which spring the closing part (16) is returned to its initial position when the actuator (17) control current / voltage is disconnected or the pressure connection to the actuator is disconnected. 5 Supply air device according to one of the preceding claims 1 to 7 or 9 or 12, characterized in that inside the shaft (15) there is a mandrel (15a3) comprising threads (C2) which engage the movable shaft part (15a2) with its threads (Cj) , to which the closing part (16) is connected to the movable shaft part (15a2), whereby the closing part (16) is moved by rotating the spindle (^ 3) and that the end plate (O) or the like is connected to the spindle (^ 3), the spindle (15a3) being rotated (O) and the valve is adjusted from the front of the supply air device, ie the side to which the flow is released from the supply air device. A method of controlling a supply air device, the method comprising flowing air through the wings of a rotating-15 tower, the method using a supply air device comprising an outer tube (11) and an inner wing tube (13) relative thereto, wherein the · · ' · Air flows through the flow paths (F) between the outer tube (11) and the vane tube (13) *, when the movable part of the tube (13) upstream of the air flow direction * · the closing part (16) is in a position allowing the outer tube (11) and the vane tube to flow 20 (13) and that when flow into said flow path is allowed, the air flows primarily directly downwards and when the flow is blocked through said flow paths, the air flow is spread over a wider area in the width direction, characterized in that the method • · ·. · ·. ·. air (arrow Lj) flows through the mass through at least a bifurcated (D1, D2) wing structure. • · «« 1 30 •? A method according to claim 14, characterized in that a wing structure with at least two circumferences is used, in which the outer circumference has more vanes than in the inner circumference and in which each wing of each circumference has a constant radius (R) over the entire length of the wing. 13 99159 Method according to Claim 14 or 15, characterized in that the closing part (16) is automatically moved to the closed position of the flow path (F) from the pressure of the air flow. 5 • · • · • · • · · · · 1 · 1 · 9 · 9 · «• · 9 9 9 9 9 9 9 9 14 99159