Patent Grant
11808270
This application is a U.S. National Stage Application of International Application No. PCT/JP2019/017548, filed on Apr. 25, 2019, the contents of which are incorporated herein by reference.
The present disclosure relates to an impeller, a multi-blade air-sending device including the impeller, and an air-conditioning apparatus including the multi-blade air-sending device.
Hitherto, a multi-blade air-sending device has a volute scroll casing and an impeller housed inside the scroll casing and configured to rotate around an axis (see, for example, Patent Literature 1). The impeller of the multi-blade air-sending device of Patent Literature 1 has a discoid backing plate, an annular rim, and blades arranged radially. The blades of the impeller are configured such that main blades and intermediate blades are alternately arranged and the inside diameters of the main and intermediate blades increase from the backing plate toward the rim. Further, each of the blades of the impeller is a sirocco blade (forward-swept blade) having a blade outlet angle of larger than or equal to 100 degrees, includes an inducer portion of a turbo blade (swept-back blade) as an inner circumferential portion of the blade, and is configured such that the ratio of the blade inside diameter to the blade outside diameter of the main blades beside the backing plate is lower than or equal to 0.7.
However, the multi-blade air-sending device of Patent Literature 1 cannot expect sufficient pressure recovery from the intermediate blades, as the ratio of an outer circumferential sirocco blade and the ratio of an inner circumferential turbo blade of each of the intermediate blades are about equal. Further, the multi-blade air-sending device of Patent Literature 1 cannot expect sufficient pressure recovery from the blades beside the rim, as the blades of the impeller are sirocco blades beside the rim.
The present disclosure is intended to solve the aforementioned problem, and has as an object to provide an impeller capable of improving pressure recovery, a multi-blade air-sending device including the impeller, and an air-conditioning apparatus including the multi-blade air-sending device.
An impeller according to an aspect of the present disclosure includes a backing plate configured to be driven by rotating, an annular rim disposed so as to face the backing plate, and a plurality of blades arranged in a circumferential direction around a virtual rotation axis of the backing plate. One end of each of the plurality of blades is connected with the backing plate, and the other end of each of the plurality of blades is connected with the rim. Each of the plurality of blades has an inner circumferential end located closer to the rotation axis in a radial direction around the rotation axis, an outer circumferential end located closer to an outer circumference than the inner circumferential end in the radial direction, a sirocco blade portion being forward-swept and including the outer circumferential end and having a blade outlet angle of larger than 90 degrees, and a turbo blade portion being swept-back and including the inner circumferential end, a first region located closer to the backing plate than a middle point in an axial direction of the rotation axis, and a second region located closer to the rim than the first region. Each of the plurality of blades is formed such that a blade length in the first region is longer than a blade length in the second region. In the first region and the second region, a ratio of the turbo blade portion in the radial direction is larger than a ratio of the sirocco blade portion in the radial direction.
A multi-blade air-sending device according to an aspect of the present disclosure includes the impeller thus configured and a scroll casing housing the impeller and having a peripheral wall formed into a volute shape and a side wall having a bellmouth forming an air inlet communicating with a space formed by the backing plate and the plurality of blades.
An air-conditioning apparatus according to an aspect of the present disclosure includes the multi-blade air-sending device thus configured.
According to an aspect of the present disclosure, in the first and second regions of the impeller, the ratio of the turbo blade portion in the radial direction is larger than the ratio of the sirocco blade portion in the radial direction. The impeller and the multi-blade air-sending device have a high ratio of the turbo blade portion in any region between the backing plate and the rim, can achieve sufficient pressure recovery through the blades, and can better improve pressure recovery than an impeller or a multi-blade air-sending device that does not include such a configuration.
In the following, an impeller, a multi-blade air-sending device, and an air-conditioning apparatus according to an embodiment are described, for example, with reference to the drawings. In the following drawings including
[Multi-Blade Air-Sending Device 100]
(Scroll Casing 40)
The scroll casing 40 houses the impeller 10 inside for use in the multi-blade air-sending device 100, and rectifies a flow of air blown out from the impeller 10. The scroll casing 40 has a scroll portion 41 and a discharge portion 42.
(Scroll Portion 41)
The scroll portion 41 forms an air trunk through which a dynamic pressure of a flow of gas generated by the impeller 10 is converted into a static pressure. The scroll portion 41 has a side wall 44a covering the impeller 10 from an axial direction of a rotation axis RS of a shaft portion 11b of the impeller 10 and having formed therein an air inlet 45 through which air is taken in and a peripheral wall 44c surrounding the impeller 10 from a radial direction of the rotation axis RS of the shaft portion 11b of the impeller 10. Further, the scroll portion 41 has a tongue 43 located between the discharge portion 42 and a scroll start portion 41a of the peripheral wall 44c to form a curved surface and configured to guide the flow of gas generated by the impeller 10 toward a discharge port 42a via the scroll portion 41. The radial direction of the rotation axis RS is a direction perpendicular to the axial direction of the rotation axis RS. An internal space of the scroll portion 41 formed by the peripheral wall 44c and the side wall 44a serves as a space in which the air blown out from the impeller 10 flows along the peripheral wall 44c.
(Side Wall 44a)
The side wall 44a is disposed at both sides of the impeller 10 in the axial direction of the rotation axis RS of the impeller 10. In the side wall 44a of the scroll casing 40, the air inlet 45 is formed so that air can flow between the impeller 10 and the outside of the scroll casing 40. The inlet port 45 is formed in a circular shape, and is disposed so that the center of the air inlet 45 and the center of the shaft portion 11b of the impeller 10 substantially coincide with each other. It should be noted that the shape of the air inlet 45 is not limited to the circular shape but may be another shape such as an elliptical shape. The scroll casing 40 of the multi-blade air-sending device 100 is a double-suction casing having side walls 44a at both sides of the backing plate 11 in the axial direction of the rotation axis RS of the shaft portion 11b with air inlets 45 formed in the side walls 44a. The multi-blade air-sending device 100 has two side walls 44a in the scroll casing 40. The two side walls 44a are formed so as to face each other via the peripheral wall 44c. More specifically, as shown in
The air inlet 45 provided in the side wall 44a is formed by a bellmouth 46. That is, the bellmouth 46 forms an air inlet 45 communicating with a space formed by the backing plate 11 and a plurality of blades 12. The bellmouth 46 rectifies a flow of gas to be suctioned into the impeller 10 and causes the flow of gas to flow into an air inlet 10e of the impeller 10. The bellmouth 46 has an opening having a diameter gradually decreasing from the outside toward the inside of the scroll casing 40. Such a configuration of the side wall 44a allows air near the air inlet 45 to smoothly flow along the bellmouth 46 and efficiently flow into the impeller 10 through the air inlet 45.
(Peripheral Wall 44c)
The peripheral wall 44c guides the flow of gas generated by the impeller 10 toward the discharge port 42a along a curved wall surface. The peripheral wall 44a is a wall provided between side walls 44a facing each other, and forms a curved surface in a direction of rotation R of the impeller 10. The peripheral wall 44c is for example disposed parallel with the axial direction of the rotation axis RS of the impeller 10 to cover the impeller 10. It should be noted that the peripheral wall 44c may be formed at a slant relative to the axial direction of the rotation axis RS of the impeller 10, and is not limited to being formed to be disposed parallel with the axial direction of the rotation axis RS. The peripheral wall 44c forms an inner circumferential surface covering the impeller 10 from the radial direction of the shaft portion 11b and facing the after-mentioned plurality of blades 12. The peripheral wall 44c faces a side of each of the blades 12 through which air is blown out from the impeller 10. As shown in
The peripheral wall 44c is formed in a volute shape. An example of the volute shape is a volute shape based on a logarithmic spiral, a spiral of Archimedes, or an involute curve. An inner peripheral surface of the peripheral wall 44c forms a curved surface smoothly curved along a circumferential direction of the impeller 10 from the scroll start portion 41a, at which the volute shape starts rolling, to the scroll end portion 41b, at which the volute shape finishes rolling. Such a configuration allows air sent out from the impeller 10 to smoothly flow through the space between the impeller 10 and the peripheral wall 44c in a direction toward the discharge portion 42. This effects an efficient rise in static pressure of air from the tongue 43 toward the discharge portion 42 in the scroll casing 40.
(Discharge Portion 42)
The discharge portion 42 forms a discharge port 42a through which a flow of gas generated by the impeller 10 and having passed through the scroll portion 41 is discharged. The discharge portion 42 is formed by a hollow pipe having a rectangular cross-section orthogonal to a flow direction of air flowing along the peripheral wall 44c. It should be noted that the cross-sectional shape of the discharge portion 42 is not limited to a rectangle. The discharge portion 42 forms a flow passage through which air sent out from the impeller 10 and flowing through a gap between the peripheral wall 44c and the impeller 10 is guided to be exhausted out of the scroll casing 40.
As shown in
(Tongue 43)
In the scroll casing 40, the tongue 43 is formed between the diffuser plate 42c of the discharge portion 42 and the scroll start portion 41a of the peripheral wall 44c. The tongue 43 is formed with a predetermined radius of curvature, and the peripheral wall 44c is smoothly connected with the diffuser plate 42c via the tongue 43. The tongue 43 reduces inflow of air from the scroll start to the scroll end of a volute flow passage. The tongue 43 is provided in an upstream part of a ventilation flue, and has a role to effect diversion into a flow of air in the direction of rotation R of the impeller 10 and a flow of air in a discharge direction from a downstream part of the ventilation flue toward the discharge port 42a. Further, a flow of air flowing into the discharge portion 42 rises in static pressure during passage through the scroll casing 40 to be higher in pressure than in the scroll casing 40. Therefore, the tongue 43 has a function of separating such different pressures.
(Impeller 10)
The impeller 10 is a centrifugal fan. The impeller 10 is driven into rotation, for example, by a motor (not illustrated). The rotation generates a centrifugal force with which the impeller 10 forcibly sends out air outward in a radial direction. The impeller 10 is rotated, for example, by the motor in a direction of rotation R indicated by an arrow. As shown in
The backing plate 11 needs only be in the shape of a plate, and may, for example, have a non-disk shape such as a polygonal shape. Further, the backing plate 11 may be formed such that as shown in
The plurality of blades 12 are arranged in a circumferential direction around a virtual rotation axis RS of the backing plate 11. One end of each of the plurality of blades 12 is connected with the backing plate 11, and the other end of each of the plurality of blades 12 is connected with the rim 13. Each of the plurality of blades 12 is disposed between the backing plate 11 and the rim 13. The plurality of blades 12 are provided on both sides of the backing plate 11 in an axial direction of a rotation axis RS of the shaft portion 11b. The blades 12 are placed at regular spacings from each other on the peripheral edge of the backing plate 11. A configuration of the blades 12 will be described in detail later.
The annular rim 13 of the impeller 10 is attached to ends of the plurality of blades 12 opposite to the backing plate 11 in the axial direction of the rotation axis RS of the shaft portion 11b. The rim 13 is disposed in the impeller 10 so as to face the backing plate 11. The rim 13 couples the plurality of blades 12 with each other, thereby maintaining a positional relationship between the tip of each blade 12 and the tip of the other blade 12 and reinforcing the plurality of blades 12.
As shown in
The first blade portion 112a is disposed on one plate surface of the backing plate 11, and the second blade portion 112b is disposed on the other plate surface of the backing plate 11. That is, the plurality of blades 12 are provided on both sides of the backing plate 11 in the axial direction of the rotation axis RS, and the first blade portion 112a and the second blade portion 112b are provided back to back with each other via the backing plate 11. In
The impeller 10 is formed in a tubular shape by the plurality of blades 12 disposed on the backing plate 11. Moreover, the impeller 10 has an air inlet 10e formed at a side of the rim 13 opposite to the backing plate 11 in the axial direction of the rotation axis RS of the shaft portion 11b and configured to cause gas to flow into a space surrounded by the backing plate 11 and the plurality of blades 12. The impeller 10 has its blades 12 and rims 13 disposed on both plate surfaces, respectively, of the backing plate 11, and has its air inlets 10e formed at both plate surfaces, respectively, of the backing plate 11.
The impeller 10 is driven into rotation around the rotation axis RS by driving of the motor (not illustrated). The rotation of the impeller 10 causes gas outside the multi-blade air-sending device 100 to be suctioned into the space surrounded by the backing plate 11 and the plurality of blades 12 through the air inlet 45 formed in the scroll casing 40 and the air inlet 10e of the impeller 10. Moreover, the rotation of the impeller 10 causes air suctioned into the space surrounded by the backing plate 11 and the plurality of blades 12 to be sent out outward in a radial direction of the impeller 10 through a space between a blade 12 and an adjacent blade 12.
[Configuration of Blades 12 in Detail]
A configuration of the blades 12 in the second blade portion 112b is similar to a configuration of the blades 12 in the first blade portion 112a. That is, in
As shown in
As shown in
As shown in
The following describes a relationship between the first blades 12A and the second blades 12B. As shown in
As shown in
Further, in the first cross-section, the diameter of a circle C2 passing through the inner circumferential ends 14B of the plurality of second blades 12B around the rotation axis RS, that is, the inside diameter of the second blades 12B, is assumed to be an inside diameter ID2 that is larger than the inside diameter ID1 (Inside Diameter ID2>Inside Diameter 101). The diameter of the circle C3 passing through the outer circumferential ends 15B of the plurality of second blades 12B around the rotation axis RS, that is, the outside diameter of the second blades 12B, is assumed to be an outside diameter OD2 that is equal to the outside diameter OD1 (Outside Diameter OD2=Outside Diameter OD1). One-half of the difference between the outside diameter OD2 and the inside diameter ID2 is equal to the blade length L2a of each of the second blades 12B in the first cross-section (Blade Length L2a=(Outside Diameter OD2−Inside Diameter ID2)/2). The blade length L2a of each of the second blades 12B in the first cross-section is shorter than the blade length Lia of each of the first blades 12A in the same cross-section (Blade Length L2a<Blade Length Lia). Note here that the ratio of the inside diameter to the outside diameter of the second blades 12B is lower than or equal to 0.7. That is, the plurality of second blades 12B are configured such that the ratio of the inside diameter ID2 formed by the inner circumferential end 14B of each of the plurality of second blades 12B to the outside diameter OD2 formed by the outer circumferential end 15B of each of the plurality of second blades 12B is lower than or equal to 0.7.
Meanwhile, as shown in
Further, let it be assumed that in the second cross-section, the diameter of the circle C7 passing through the inner circumferential ends 14B of the second blades 12B around the rotation axis RS is an inside diameter ID4. The inside diameter ID4 is equal to the inside diameter ID3 in the same cross-section (Inside Diameter ID4=Inside Diameter ID3). The diameter of the circle C8 passing through the outer circumferential ends 15B of the second blades 12B around the rotation axis RS is assumed to be an outside diameter OD4. The outside diameter OD4 is equal to the outside diameter OD3 in the same cross-section (Outside Diameter OD4=Outside Diameter OD3). One-half of the difference between the outside diameter OD4 and the inside diameter ID4 is equal to the blade length L2b of each of the second blades 12B in the second cross-section (Blade Length L2b=(Outside Diameter OD4−Inside Diameter ID4)/2). The blade length L2b of each of the second blades 12B in the second cross-section is equal to the blade length L1b of each of the first blades 12A in the same cross-section (Blade Length L2b=Blade Length Lib).
When viewed from an angle parallel with the rotation axis RS, the first blades 12A in the second cross-section shown in
Similarly, when viewed from an angle parallel with the rotation axis RS, the second blades 12B in the second cross-section shown in
Note here that as mentioned above, the ratio of the inside diameter ID1 to the outside diameter OD1 of the first blades 12A is lower than or equal to 0.7. Since the blades 12 are configured such that Inside Diameter ID3≥Inside Diameter ID1, Inside Diameter ID4≥Inside Diameter ID2, and Inside Diameter ID2>Inside Diameter ID1, the inside diameter of the first blades 12A can be the blade inside diameter of the blades 12. Further, since the blades 12 are configured such that Outside Diameter OD3=Outside Diameter OD1, Outside Diameter OD4=Outside Diameter OD2, and Outside Diameter OD2=Outside Diameter OD1, the outside diameter of the first blades 12A can be the blade outside diameter of the blades 12. Moreover, in a case in which the blades 12 forming the impeller 10 are seen as a whole, the blades 12 are configured such that the ratio of the blade inside diameter to the blade outside diameter of the blades 12 is lower than or equal to 0.7. It should be noted that the blade inside diameter of the plurality of blades 12 is formed by the inner circumferential end of each of the plurality of blades 12. That is, the blade inside diameter of the plurality of blades 12 is formed by the leading edges 14A1 of the plurality of blades 12. Further, the blade outside diameter of the plurality of blades 12 is formed by the outer circumferential end of each of the plurality of blade 12. That is, the blade outside diameter of the plurality of blades 12 is formed by the trailing edges 15A1 and 15B1 of the plurality of blades 12.
[Configuration of First Blades 12A and Second Blades 12B]
In a comparison between the first cross-section shown in
As shown in
In the radial direction of the impeller 10, a region forming the first sirocco blade portion 12A1 of each of the first blades 12A is defined as a first sirocco region 12A11, and a region forming the first turbo blade portion 12A2 of each of the first blades 12A is defined as a first turbo region 12A21. Each of the first blades 12A is configured such that the first turbo region 12A21 is larger than the first sirocco region 12A11 in the radial direction of the impeller 10. Moreover, in both the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region, the impeller 10 has the relationship “First Sirocco Region 12A11<First Turbo Region 12A21” in the radial direction of the impeller 10. That is, the impeller 10 and each of the first blades 12A are configured such that in both the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region, a ratio of the first turbo blade portion 12A2 is larger than a ratio of the first sirocco blade portion 12A1 in the radial direction of the impeller 10.
Similarly, as shown in
In the radial direction of the impeller 10, a region forming the second sirocco blade portion 12B1 of each of the second blades 12B is defined as a second sirocco region 12B11, and a region forming the second turbo blade portion 12B2 of each of the second blades 12B is defined as a second turbo region 12B21. Each of the second blades 12B is configured such that the second turbo region 12B21 is larger than the second sirocco region 12B11 in the radial direction of the impeller 10. Moreover, in both the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region, the impeller 10 has the relationship “Second Sirocco Region 12B11<Second Turbo Region 12B21” in the radial direction of the impeller 10. That is, the impeller 10 and each of the second blades 12B are configured such that in both the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region, a ratio of the second turbo blade portion 12B2 is larger than a ratio of the second sirocco blade portion 12B1 in the radial direction of the impeller 10.
According to the foregoing configuration, the plurality of blades 12 are configured such that in both the backing-plate-side blade region 122a and the rim-side blade region 122b, a region of a turbo blade portion is larger than a region of a sirocco blade portion in the radial direction of the impeller 10. That is, the plurality of blades 12 are configured such that in both the backing-plate-side blade region 122a and the rim-side blade region 122b, a ratio of the turbo blade portion is larger than a ratio of the sirocco blade portion in the radial direction of the impeller 10, and have the relationship “Sirocco Region<Turbo Region”. In other words, each of the plurality of blades 12 is configured such that in the first region and the second region, a ratio of the turbo blade portion in the radial direction is larger than a ratio of the sirocco blade portion in the radial direction.
As shown in
As shown in
Further, as shown in
Although not illustrated in
As shown in
When a spacing between two of the plurality of blades 12 adjacent to each other in the circumferential direction is defined as a blade spacing, the blade spacing between a plurality of blades 12 widens from the leading edges 14A1 toward the trailing edges 15A1 as shown in
[Relationship Between Impeller 10 and Scroll Casing 40]
The impeller 10 is configured such that the first turbo region 12A21 is larger than the first sirocco region 12A11 in the radial direction relative to the rotation axis RS. That is, the impeller 10 and each of the first blades 12A are configured such that the ratio of the first turbo blade portion 12A2 is larger than the ratio of the first sirocco blade portion 12A1 in the radial direction relative to the rotation axis RS, and have the relationship “First Sirocco Blade Portion 12A1<First Turbo Blade Portion 12A2”. The relationship between the ratio of the first sirocco blade portion 12A1 and the ratio of the first turbo blade portion 12A2 in the radial direction of the rotation axis RS holds in both the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region.
Furthermore, a region of portions of the plurality of blades 12 situated closer to the outer circumference than the inside diameter BI of the bellmouth 46 in the radial direction relative to the rotation axis RS when viewed from an angle parallel with the rotation axis RS is defined as an outer circumferential region 12R. It is desirable that the impeller 10 be configured such that in the outer circumferential region 12R, too, the ratio of the first turbo blade portion 12A2 is larger than the ratio of the first sirocco blade portion 12A1. That is, in the outer circumferential region 12R of the impeller 10 situated closer to the outer circumference than the inside diameter BI of the bellmouth 46 when viewed from an angle parallel with the rotation axis RS, a first turbo region 12A21a is larger than the first sirocco region 12A11 in the radial direction relative to the rotation axis RS. The first turbo region 12A21a is a region of the first turbo region 12A21 situated closer to the outer circumference than the inside diameter BI of the bellmouth 46 when viewed from an angle parallel with the rotation axis RS. Moreover, in a case in which a first turbo blade portion 12A2 forming the first turbo region 12A21a is a first turbo blade portion 12A2a, it is desirable that the outer circumferential region 12R of the impeller 10 be configured such that a ratio of the first turbo blade portion 12A2a is larger than the ratio of the first sirocco blade portion 12A1. The relationship between the ratio of the first sirocco blade portion 12A1 and the ratio of the first turbo blade portion 12A2a in the outer circumferential region 12R holds in both the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region.
Similarly, the impeller 10 is configured such that the second turbo region 12B21 is larger than the second sirocco region 12B11 in the radial direction relative to the rotation axis RS. That is, the impeller 10 and each of the second blades 12B are configured such that the ratio of the second turbo blade portion 12B2 is larger than the ratio of the second sirocco blade portion 12B1 in the radial direction relative to the rotation axis RS, and have the relationship “Second Sirocco Blade Portion 12B1<Second Turbo Blade Portion 12B2”. The relationship between the ratio of the second sirocco blade portion 12B1 and the ratio of the second turbo blade portion 12B2 in the radial direction of the rotation axis RS holds in both the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region.
Furthermore, it is desirable that the impeller 10 be configured such that in the outer circumferential region 12R, too, the ratio of the second turbo blade portion 12B2 is larger than the ratio of the second sirocco blade portion 12B1. That is, in the outer circumferential region 12R of the impeller 10 situated closer to the outer circumference than the inside diameter BI of the bellmouth 46 when viewed from an angle parallel with the rotation axis RS, a second turbo region 12B21a is larger than the second sirocco region 12B11 in the radial direction relative to the rotation axis RS. The second turbo region 12B21a is a region of the second turbo region 12B21 situated closer to the outer circumference than the inside diameter BI of the bellmouth 46 when viewed from an angle parallel with the rotation axis RS. Moreover, in a case in which a second turbo blade portion 12B2 forming the second turbo region 12B21a is a second turbo blade portion 12B2a, it is desirable that the outer circumferential region 12R of the impeller 10 be configured such that a ratio of the second turbo blade portion 12B2a is larger than the ratio of the second sirocco blade portion 12B1. The relationship between the ratio of the second sirocco blade portion 12B1 and the ratio of the second turbo blade portion 12B2a in the outer circumferential region 12R holds in both the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region.
As shown in
Further, as shown in
Let it be assumed that as shown in
The motor 50 is disposed adjacent to the side wall 44a of the scroll casing 40. The motor 50 has a motor shaft 51 extending on the rotation axis RS of the impeller 10 and being inserted in the scroll casing 40 through a side surface of the scroll casing 40.
The backing plate 11 is disposed so as to be perpendicular to the rotation axis RS along the side wall 44a of the scroll casing 40 facing the motor 50. The backing plate 11 has provided in a central part thereof a shaft portion 11b with which the motor shaft 51 is connected, and the motor shaft 51 is fixed to the shaft portion 11b of the backing plate 11 while being inserted in the scroll casing 40. The motor shaft 51 of the motor 50 is connected with the backing plate 11 of the impeller 10 to be fixed.
Once the motor 50 is brought into operation, the plurality of blades 12 rotate around the rotation axis RS via the motor shaft 51 and the backing plate 11. This causes outside air to be suctioned into the impeller 10 through the air inlet 45 and blown out into the scroll casing 40 by a booster action of the impeller 10. The air blown out into the scroll casing 40 recovers its static pressure by having its speed reduced in an expanded air trunk formed by the peripheral wall 44c of the scroll casing 40, and is blown out to the outside through the discharge port 42a shown in
As shown in
Further, the multi-blade air-sending device 100B is configured such that an outer peripheral wall 52b forming the outermost diameter MO2a of the motor 50B is located between the virtual extended surface VF1 formed by extending the blade inside diameter of the blades 12 beside the backing plate 11 in the axial direction of the rotation axis RS and a virtual extended surface VF3 formed by extending the blade inside diameter of the blades 12 beside the rim 13 in the axial direction of the rotation axis RS. Further, the outer peripheral wall 52b forming the outermost diameter MO2a of the motor 50B is disposed in such a location as to face the first turbo blade portions 12A2 and the second turbo blade portions 12B2 in the axial direction of the rotation axis RS. More specifically, the outermost diameter MO2a of the motor 50B is larger than the inside diameter ID1 of the plurality of first blades 12A beside the backing plate 11 and smaller than the inside diameter ID3 of the plurality of first blades 12A beside the rim 13. That is, the outermost diameter MO2a of the motor 50B is formed to be larger than the blade inside diameter of the plurality of blades 12 beside the backing plate 11 and smaller than the blade inside diameter of the plurality of blades 12 beside the rim 13. Further, the outer peripheral wall 52b forming the outermost diameter MO2a of the motor 50B is located in a region of the first turbo blade portions 12A2 and the second turbo blade portions 12B2 between the aforementioned circles Cia and C7a when viewed from an angle parallel with the rotation axis RS.
[Working Effects of Impeller 10 and Multi-Blade Air-Sending Device 100]
The impeller 10 and the multi-blade air-sending device 100 are configured such that in the first and second regions of the impeller 10, a ratio of the turbo blade portion in the radial direction is larger than a ratio of the sirocco blade portion in the radial direction. Since the impeller 10 and the multi-blade air-sending device 100 are configured such that the ratio of the turbo blade portion is high in any region between the backing plate 11 and the rim 13, sufficient pressure recovery can be achieved through the plurality of blades 12. Therefore, the impeller 10 and the multi-blade air-sending device 100 can better improve pressure recovery than an impeller or a multi-blade air-sending device that does not include such a configuration. As a result, the impeller 10 can improve the efficiency of the multi-blade air-sending device 100. Furthermore, by including the foregoing configuration, the impeller 10 can reduce leading edge separation of a flow of gas beside the rim 13.
Further, each of the plurality of blades 12 has a radial blade portion serving a portion of connection between the turbo blade portion and the sirocco blade portion and having a blade angle of 90 degrees. By having the radial blade portion between the turbo blade portion and the sirocco blade portion, the impeller 10 is free of an abrupt angle change in the portion of connection between the sirocco blade portion and the turbo blade portion. Therefore, the impeller 10 can reduce pressure fluctuations in the scroll casing 40, increase the fan efficiency of the multi-blade air-sending device 100, and further reduce noise.
Further, the plurality of blades 12 are configured such that at least one of the plurality of second blades 12B is disposed between two of the plurality of first blades 12A adjacent to each other in the circumferential direction. Since the impeller 10 and the multi-blade air-sending device 100 are configured such that in each of the second blades 12B, too, the ratio of the turbo blade portion is high in any region between the backing plate 11 and the rim 13, sufficient pressure recovery can be achieved through the second blades 12B. Therefore, the impeller 10 and the multi-blade air-sending device 100 can better improve pressure recovery than an impeller or a multi-blade air-sending device that does not include such a configuration. As a result, the impeller 10 can improve the efficiency of the multi-blade air-sending device 100. Furthermore, by including the foregoing configuration, the impeller 10 can reduce leading edge separation of a flow of gas beside the rim 13.
Further, the plurality of second blades 12B are formed such that a ratio of an inside diameter formed by the inner circumferential end 14B of each of the plurality of second blades 12B to an outside diameter formed by the outer circumferential end 15B of each of the plurality of second blades 12B is lower than or equal to 0.7. Since the impeller 10 and the multi-blade air-sending device 100 are configured such that in each of the second blades 12B, too, the ratio of the turbo blade portion is high in any region between the backing plate 11 and the rim 13, sufficient pressure recovery can be achieved through the second blades 12B. Therefore, the impeller 10 and the multi-blade air-sending device 100 can better improve pressure recovery than an impeller or a multi-blade air-sending device that does not include such a configuration. As a result, the impeller 10 can improve the efficiency of the multi-blade air-sending device 100. Furthermore, by including the foregoing configuration, the impeller 10 can reduce leading edge separation of a flow of gas beside the rim 13.
Further, the plurality of blades 12 are configured such that in a portion of the plurality of blades 12 situated closer to the outside than the inside diameter BI of the bellmouth 46 in the radial direction relative to the rotation axis RS, a ratio of a region of the turbo blade portion in the radial direction of the backing plate 11 is larger than a ratio of a region of the sirocco blade portion in the radial direction of the backing plate 11. The plurality of blades 12 is configured such that such a configuration holds in any region between the backing plate 11 and the rim 13. By including such a configuration, the plurality of blades 12 can increase the amount of air that is suctioned in a portion of the blades 12 inside the inside diameter BI of the bellmouth 46. Further, by increasing the ratio of the turbo blade portion in the portion of the plurality of blades 12 situated closer to the outside than the inside diameter BI of the bellmouth 46, the plurality of blades 12 can increase the volume of air that is emitted from the impeller 10. Furthermore, by having such a configuration, the plurality of blades 12 can increase pressure recovery in the scroll casing 40 of the multi-blade air-sending device 100 and improve fan efficiency.
Further, the inside diameter BI of the bellmouth 46 is formed to be larger than the blade inside diameter of the plurality of blades 12 beside the backing plate 11 and smaller than the blade inside diameter of the plurality of blades 12 beside the rim 13. Therefore, the multi-blade air-sending device 100 can reduce interference between a flow of suctioned gas flowing in through the air inlet 45 of the bellmouth 46 and the blades 12 beside the rim 13 and further reduce noise.
Further, the inside diameter BI of the bellmouth 46 is formed to be larger than the blade inside diameter of the plurality of second blades 12B beside the backing plate 11 and smaller than the blade inside diameter of the plurality of second blades 12B beside the rim 13. Therefore, the multi-blade air-sending device 100 can reduce interference between a flow of suctioned gas flowing in through the air inlet 45 of the bellmouth 46 and the second blades 12B beside the rim 13 and further reduce noise.
Further, the distance MS, which is the shortest distance between the plurality of blades 12 and the peripheral wall 44c, is more than twice as long as the radial length of the sirocco blade portion. Therefore, the multi-blade air-sending device 100 can achieve pressure recovery through the turbo blade portion, increase the distance between the scroll casing 40 and the impeller 10 in a place where they are closest to each other, and can therefore reduce noise.
Further, the multi-blade air-sending device 100 is formed such that the outside diameter MO1 of an end portion 50a of the motor 50 is larger than the blade inside diameter of the plurality of blades 12 beside the backing plate 11 and smaller than the blade inside diameter of the plurality of blades 12 beside the rim 13. By including such a configuration, the multi-blade air-sending device 100 causes a flow of gas from the vicinity of the motor 50 to be diverted into the axial direction of the rotation axis RS of the impeller 10 and causes air to be smoothly flow into the scroll casing 40, thereby making it possible to increase the volume of air that is emitted from the impeller 10. Furthermore, by having such a configuration, the multi-blade air-sending device 100 can increase pressure recovery in the scroll casing 40 and improve fan efficiency.
Further, the multi-blade air-sending device 100A is formed such that the outside diameter MO of the motor 50A is larger than the blade inside diameter of the plurality of blades 12 beside the backing plate 11 and smaller than the blade inside diameter of the plurality of blades 12 beside the rim 13. By including such a configuration, the multi-blade air-sending device 100A causes a flow of gas from the vicinity of the motor 50A to be diverted into the axial direction of the rotation axis RS of the impeller 10 and causes air to be smoothly flow into the scroll casing 40, thereby making it possible to increase the volume of air that is emitted from the impeller 10. Furthermore, by having such a configuration, the multi-blade air-sending device 100A can increase pressure recovery in the scroll casing 40 and improve fan efficiency.
Further, the multi-blade air-sending device 100B is formed such that the outside diameter MO2a of the motor 50B is larger than the blade inside diameter of the plurality of blades 12 beside the backing plate 11 and smaller than the blade inside diameter of the plurality of blades 12 beside the rim 13 and the outside diameter MO1a of an end portion 50a of the motor 50B is formed to be smaller than the blade inside diameter of the plurality of blades 12 beside the backing plate 11. By including such a configuration, the multi-blade air-sending device 100B can better cause air to be smoothly flow into the scroll casing 40 and increase the volume of air that is emitted from the impeller 10 than the multi-blade air-sending device 100A or other devices. Furthermore, by having such a configuration, the multi-blade air-sending device 100B can better increase pressure recovery in the scroll casing 40 and improve fan efficiency than the multi-blade air-sending device 100A or other devices.
[Multi-Blade Air-Sending Device 100C]
As mentioned above, the plurality of blades 12 form an inclined portion 141A inclined such that the leading edges 14A1 extend away from the rotation axis RS so that the blade inside diameter increases from the backing plate 11 toward the rim 13. That is, the plurality of blades 12 form an inclined portion 141A inclined such that the inner circumferential ends 14A extend away from the rotation axis RS so that the blade inside diameter increases from the backing plate 11 toward the rim 13. Similarly, the plurality of blades 12 form an inclined portion 141B inclined such that the leading edges 14B1 extend away from the rotation axis RS so that the blade inside diameter increases from the backing plate 11 toward the rim 13. That is, the plurality of blades 12 form an inclined portion 141B inclined such that the inner circumferential ends 14B extend away from the rotation axis RS so that the blade inside diameter increases from the backing plate 11 toward the rim 13. The plurality of blades 12 have gradients formed on the inner circumference by the inclined portion 141A and the inclined portion 141B.
The inclined portion 141A is inclined relative to the rotation axis RS. The inclined portion 141A has an angle of inclination preferably larger than 0 degree and smaller than or equal to 60 degrees or more preferably larger than 0 degree and smaller than or equal to 45 degrees. That is, an angle of inclination θ1 between the inclined portion 141A and the rotation axis RS is configured to preferably satisfy the relationship “0 degree<θ1≤60 degrees” or more preferably satisfy the relationship “0 degree<θ1≤45 degrees”. In
Similarly, the inclined portion 141B is inclined relative to the rotation axis RS. The inclined portion 141B has an angle of inclination preferably larger than 0 degree and smaller than or equal to 60 degrees or more preferably larger than 0 degree and smaller than or equal to 45 degrees. That is, an angle of inclination θ2 between the inclined portion 141B and the rotation axis RS is configured to preferably satisfy the relationship “0 degree<θ2≤60 degrees” or more preferably satisfy the relationship “0 degree<θ2≤45 degrees”. In
The blade height WH shown in
[Working Effects of Impeller 10C and Multi-Blade Air-Sending Device 100C]
As shown in
On the other hand, as shown in
Angles of inclination of the inclined portions 141A and 141B of the multi-blade air-sending device 1000 may be set as appropriate. Although increasing the angles of inclination of the inclined portions 141A and 141B makes it possible to ensure a wide area of the leading edges of the blades 12 relative to a flow of gas, it is necessary to increase the sizes of the impeller 10C and the multi-blade air-sending device 100C in the radial direction to increase the angles of inclination while ensuring the predetermined blade height WH. To ensure a wide area of the leading edges of the blades 12 while suppressing upsizing of the impeller 10C and the multi-blade air-sending device 100C, it is desirable to set the angles of inclination of the inclined portions 141A and 141B to be smaller than or equal to 60 degrees. Further, to achieve a further reduction in size of the impeller 10C and the multi-blade air-sending device 100C, it is desirable to set the angles of inclination of the inclined portions 141A and 141B to be smaller than or equal to 45 degrees.
[Multi-Blade Air-Sending Device 100D]
As mentioned above, the plurality of blades 12 form an inclined portion 141A inclined such that the leading edges 14A1 extend away from the rotation axis RS so that the blade inside diameter increases from the backing plate 11 toward the rim 13. Similarly, the plurality of blades 12 form an inclined portion 141B inclined such that the leading edges 14B1 extend away from the rotation axis RS so that the blade inside diameter increases from the backing plate 11 toward the rim 13. The plurality of blades 12 have gradients formed on the inner circumference by the inclined portion 141A and the inclined portion 141B.
The inclined portion 141A is inclined relative to the rotation axis RS. The inclined portion 141A has an angle of inclination preferably larger than 0 degree and smaller than or equal to 60 degrees or more preferably larger than 0 degree and smaller than or equal to 45 degrees. That is, an angle of inclination θ1 between the inclined portion 141A and the rotation axis RS is configured to preferably satisfy the relationship “0 degree<θ1≤60 degrees” or more preferably satisfy the relationship “0 degree<θ1≤45 degrees”. Similarly, the inclined portion 141B is inclined relative to the rotation axis RS. The inclined portion 141B has an angle of inclination preferably larger than 0 degree and smaller than or equal to 60 degrees or more preferably larger than 0 degree and smaller than or equal to 45 degrees. That is, an angle of inclination θ2 between the inclined portion 141B and the rotation axis RS is configured to preferably satisfy the relationship “0 degree<θ2≤60 degrees” or more preferably satisfy the relationship “0 degree<θ2≤45 degrees”.
The blade height WH shown in
The plurality of blades 12 have linear portions 141C1 provided at the leading edges 14A1 between the backing plate 11 and the rim 13. The linear portions 141C1 are provided beside the backing plate 11 between the backing plate 11 and the rim 13. Accordingly, the leading edge 14A1 of a first blade 12A is formed by a linear portion 141C1 provided beside the backing plate 11 and an inclined portion 141A provided beside the rim 13. The impeller 10D of the multi-blade air-sending device 100D is configured such that an inside diameter IDc1 formed by the linear portions 141C1 of the leading edges 14A1 has a certain size in the axial direction of the rotation axis RS.
Similarly, the plurality of blades 12 have linear portions 141C2 provided at the leading edges 14B1 between the backing plate 11 and the rim 13. The linear portions 141C2 are provided beside the backing plate 11 between the backing plate 11 and the rim 13. Accordingly, the leading edge 14B1 of a second blade 12B is formed by a linear portion 141C2 provided beside the backing plate 11 and an inclined portion 141B provided beside the rim 13. The impeller 10D of the multi-blade air-sending device 100D is configured such that an inside diameter IDc2 formed by the linear portions 141C2 of the leading edges 14B1 has a certain size in the axial direction of the rotation axis RS.
[Working Effects of Impeller 10D and Multi-Blade Air-Sending Device 100D]
As shown in
[Multi-Blade Air-Sending Device 100E]
As mentioned above, the plurality of blades 12 form an inclined portion 141A inclined such that the leading edges 14A1 extend away from the rotation axis RS so that a blade inside diameter IDe increases from the backing plate 11 toward the rim 13. Further, the plurality of blades 12 form an inclined portion 141A2 inclined such that the leading edges 14A1 extend away from the rotation axis RS so that the blade inside diameter IDe increases from the backing plate 11 toward the rim 13. The inclined portion 141A2 is provided beside the backing plate 11 between the backing plate 11 and the rim 13. Accordingly, the leading edge 14A1 of a first blade 12A is formed by a inclined portion 141A2 provided beside the backing plate 11 and an inclined portion 141A provided beside the rim 13. That is, a first blade 12A of the plurality of blades 12 has two inclined portions, namely an inclined portion 141A and an inclined portion 141A2, between the backing plate 11 and the rim 13. A first blade 12A of the plurality of blades 12 is not limited to being configured to have two inclined portions, namely an inclined portion 141A and an inclined portion 141A2, but needs only have two or more inclined portions.
Similarly, the plurality of blades 12 form an inclined portion 141B inclined such that the leading edges 14B1 extend away from the rotation axis RS so that the blade inside diameter IDe increases from the backing plate 11 toward the rim 13. Further, the plurality of blades 12 form an inclined portion 141B2 inclined such that the leading edges 14B1 extend away from the rotation axis RS so that the blade inside diameter IDe increases from the backing plate 11 toward the rim 13. The inclined portion 141B2 is provided beside the backing plate 11 between the backing plate 11 and the rim 13. Accordingly, the leading edge 14B1 of a second blade 12B is formed by an inclined portion 141B2 provided beside the backing plate 11 and an inclined portion 141B provided beside the rim 13. That is, a second blade 12B of the plurality of blades 12 has two inclined portions, namely an inclined portion 141B and an inclined portion 141B2, between the backing plate 11 and the rim 13. A second blade 12B of the plurality of blades 12 is not limited to being configured to have two inclined portions, namely an inclined portion 141B and an inclined portion 141B2, but needs only have two or more inclined portions. The plurality of blades 12 have gradients formed on the inner circumference by the inclined portion 141A, the inclined portion 141A2, the inclined portion 141B, and the inclined portion 141B2.
At least either the inclined portion 141A or the inclined portion 141A2 is inclined relative to the rotation axis RS. The inclined portion 141A and/or the inclined portion 141A2 has/have an angle of inclination preferably larger than 0 degree and smaller than or equal to 60 degrees or more preferably larger than 0 degree and smaller than or equal to 45 degrees. That is, an angle of inclination θ1 between the inclined portion 141A and the rotation axis RS is configured to preferably satisfy the relationship “0 degree<θ1≤60 degrees” or more preferably satisfy the relationship “0 degree<θ1≤45 degrees”. Alternatively, an angle of inclination θ11 between the inclined portion 141A2 and the rotation axis RS is configured to preferably satisfy the relationship “0 degree<θ11≤60 degrees” or more preferably satisfy the relationship “0 degree<θ11≤45 degrees”. In
The angle of inclination θ1 of the inclined portion 141A and the angle of inclination θ11 of the inclined portion 141A2 are different angles. In a case in which a first blade 12A has two or more inclined portions, the angle of inclination of each inclined portion is different from that of the other. There is no limit on a relationship between the magnitude of the angle of inclination θ1 of the inclined portion 141A and the magnitude of the angle of inclination θ11 of the inclined portion 141A2. For example, as shown in
Similarly, at least either the inclined portion 141B or the inclined portion 141B2 is inclined relative to the rotation axis RS. The inclined portion 141B and/or the inclined portion 141B2 has/have an angle of inclination preferably larger than 0 degree and smaller than or equal to 60 degrees or more preferably larger than 0 degree and smaller than or equal to 45 degrees. That is, an angle of inclination θ2 between the inclined portion 141B and the rotation axis RS is configured to preferably satisfy the relationship “0 degree<θ2≤60 degrees” or more preferably satisfy the relationship “0 degree<θ2≤45 degrees”. Alternatively, an angle of inclination θ22 between the inclined portion 141B2 and the rotation axis RS is configured to preferably satisfy the relationship “0 degree<θ22≤60 degrees” or more preferably satisfy the relationship “0 degree<θ22≤45 degrees”. In
The angle of inclination θ2 of the inclined portion 141B and the angle of inclination θ22 of the inclined portion 141B2 are different angles. In a case in which a second blade 12B has two or more inclined portions, the angle of inclination of each inclined portion is different from that of the other. There is no limit on a relationship between the magnitude of the angle of inclination θ2 of the inclined portion 141B and the magnitude of the angle of inclination θ22 of the inclined portion 141B2. For example, as shown in
The blade height WH shown in
[Working Effects of Impeller 10E and Multi-Blade Air-Sending Device 100E]
As shown in
[Multi-Blade Air-Sending Device 100F]
The impeller 10F of the multi-blade air-sending device 100F according to Embodiment 3 has a step portion 12D formed at an end portion 12t of a turbo blade portion facing the rim 13. In the following, as shown in
A second blade 12B has a step portion 12D formed therein, too, although the step portion 12D of the second blade 12B is not illustrated, as it is similar in configuration to that of the first blade 12A. The step portion 12D is formed at an end portion 12t of the second turbo blade portion 12B2 facing the rim 13, too. That is, the step portion 12D is formed at an end portion 12t of the inclined portion 141B facing the rim 13. The step portion 12D is a portion in which a wall forming the second blade 12B is formed in a notched state. The step portion 12D is a portion in which a portion of joining between the leading edge 14B1 of the second blade 12B and the end portion 12t of the second turbo blade portion 12B2 facing the rim 13 is formed in a notched state.
The plurality of blades 12 of the multi-blade air-sending device 100F according to Embodiment 3 are formed such that a blade outside diameter formed by the outer circumferential end of each of the plurality of blades 12 is larger than the inside diameter BI of the bellmouth 46. Moreover, as shown in
[Working Effects of Impeller 10F and Multi-Blade Air-Sending Device 100F]
The impeller 10F and the multi-blade air-sending device 100F have a step portion formed at an end portion 12t of a turbo blade portion facing the rim 13. The step portion 12D allows the impeller 10F and the multi-blade air-sending device 100F to widen the gap between a bellmouth 46 and a blade 12. Therefore, the impeller 10F and the multi-blade air-sending device 100F can suppress an increase in velocity of a flow of gas in the gap between the bellmouth 46 and the blade 12, thus making it possible to reduce noise generated by the flow of gas passing through the gap between the bellmouth 46 and the blade 12.
Further, the impeller 10F and the multi-blade air-sending device 100F allow the bellmouth 46 to be brought closer to the impeller 10F than in a case in which a blade 12 has no step portion 12D. Moreover, the impeller 10F and the multi-blade air-sending device 100F can reduce the gap between the bellmouth 46 and the blade 12 by bringing the bellmouth 46 close to the impeller 10F. As a result, the impeller 10F and the multi-blade air-sending device 100F can reduce leakage of suctioned air, that is, the amount of air that does not pass through the space between adjacent blades 12 of the impeller 10F. Since the bellmouth 46 and the side edge portion 12D1 are disposed so as to face each other as shown in
[Multi-Blade Air-Sending Device 100G]
As shown in
Each of the first blades 12A has the relationship “Blade Length L1a>Blade Length L1b”. That is, each of the first blades 12A is formed such that its blade length decreases from the backing plate 11 toward the rim 13 in the axial direction of the rotation axis RS. Moreover, as shown in
Each of the first blades 12A has a first sirocco blade portion 12A1 being forward-swept and a first turbo blade portion 12A2 being swept-back. Each of the first blades 12A is configured such that the first turbo region 12A21 is larger than the first sirocco region 12A11 in the radial direction of the impeller 10. That is, the impeller 10 and each of the first blades 12A are configured such that in both the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region, a ratio of the first turbo blade portion 12A2 is larger than a ratio of the first sirocco blade portion 12A1 in the radial direction of the impeller 10.
When a spacing between two of the plurality of blades 12 adjacent to each other in the circumferential direction is defined as a blade spacing, the blade spacing between a plurality of blades 12 widens from the leading edges 14A1 toward the trailing edges 15A1 as shown in
As shown in
[Working Effects of Impeller 10G and Multi-Blade Air-Sending Device 100G]
The impeller 10G and the multi-blade air-sending device 100G can bring about effects similar to those of the multi-blade air-sending device 100 and the impeller 10 according to Embodiment 1. For example, the impeller 10G and the multi-blade air-sending device 100G are configured such that in any region between the backing plate 11 and the rim 13, a ratio of a region of the first turbo blade portion 12A2 in the radial direction of the backing plate 11 is larger than a ratio of a region of the first sirocco blade portion 12A1 in the radial direction of the backing plate 11. Since the impeller 10G and the multi-blade air-sending device 100G are configured such that the ratio of the turbo blade portion is high in any region between the backing plate 11 and the rim 13, sufficient pressure recovery can be achieved through the plurality of blades 12. Therefore, the impeller 10G and the multi-blade air-sending device 100G can better improve pressure recovery than an impeller or a multi-blade air-sending device that does not include such a configuration. As a result, the impeller 10G can improve the efficiency of the multi-blade air-sending device 100G. Furthermore, by including the foregoing configuration, the impeller 10G can reduce leading edge separation of a flow of gas beside the rim 13.
Embodiments 1 to 4 have been described by taking as an example a multi-blade air-sending device 100 including a double-suction impeller 10 having a plurality of blades 12 formed on both sides of a backing plate 11. However, Embodiments 1 to 4 are also applicable to a multi-blade air-sending device 100 including a single-suction impeller 10 having a plurality of blades 12 formed only on one side of a backing plate 11.
[Air-Conditioning Apparatus 140]
The air-conditioning apparatus 140 according to Embodiment 5 includes any one or more of the multi-blade air-sending devices 100 to 100G according to Embodiments 1 to 4 and a heat exchanger 15 disposed in such a location as to face a discharge port 42a of the multi-blade air-sending device 100. Further, the air-conditioning apparatus 140 according to Embodiment 5 includes a case 16 installed above a ceiling of a room to be air-conditioned. In the following description, the term “multi-blade air-sending device 100” indicates the use of any one of the multi-blade air-sending devices 100 to 100G according to Embodiments 1 to 4. Further, although, in
(Case 16)
As shown in
Inside the case 16, the multi-blade air-sending device 100 and the heat exchanger 15 are housed. The multi-blade air-sending device 100 includes an impeller 10, a scroll casing 40 having a bellmouth 46 formed therein, and a motor 50. The motor 50 is supported by a motor support 9a fixed to the upper surface portion 16a of the case 16. The motor 50 has a motor shaft 51. The motor shaft 51 is disposed so as to extend parallel to the side surface portion 16c having the case air inlet 18 formed therein and the side surface portion 16c having the case discharge port 17 formed therein. As shown in
As shown in
The heat exchanger 15 is disposed in such a location as to face the discharge port 42a of the multi-blade air-sending device 100, and is disposed in the case 16 so as to be on an air trunk of air to be discharged by the multi-blade air-sending device 100. The heat exchanger 15 adjusts the temperature of air that is suctioned into the case 16 through the case air inlet 18 and blown out into the air-conditioned space through the case discharge port 17. As the heat exchanger 15, a heat exchanger of a publicly-known structure can be applied. The case air inlet 18 needs only be formed in a location perpendicular to the axial direction of the rotation axis RS of the multi-blade air-sending device 100. For example, the case air inlet 18 may be formed in the lower surface portion 16b.
Rotation of the impeller 10 of the multi-blade air-sending device 100 causes the air in the air-conditioned space to be suctioned into the case 16 through the case air inlet 18. The air suctioned into the case 16 is guided toward the bellmouth 46 and suctioned into the impeller 10. The air suctioned into the impeller 10 is blown out outward in the radial direction of the impeller 10. The air blown out from the impeller 10 passes through the inside of the scroll casing 40, blown out of the scroll casing 40 through the discharge port 42a, and then supplied to the heat exchanger 15. The air supplied to the heat exchanger 15 is subjected to temperature and humidity control by, during passage through the heat exchanger 15, exchanging heat with refrigerant flowing through the inside of the heat exchanger 15. The air having passed through the heat exchanger 15 is blown out to the air-conditioned space through the case discharge port 17.
The air-conditioning apparatus 140 according to Embodiment 5 includes any one of the multi-blade air-sending devices 100 to 100G according to Embodiments 1 to 4. Therefore, the air-conditioning apparatus 140 can bring about effects similar to those of any of Embodiments 1 to 4.
Each of Embodiment 1 to 5 may be implemented in combination with the other. Further, the configurations shown in the foregoing embodiments show examples and may be combined with another publicly-known technology, and parts of the configurations may be omitted or changed, provided such omissions and changes do not depart from the scope. For example, an embodiment describes an impeller 10 or other devices formed by the backing-plate-side blade region 122a serving as the first region and the rim-side blade region 122b serving as the second region. The impeller 10 is not limited to an impeller formed solely by the first region and the second region. The impeller 10 may further have another region as well as the first region and the second region. For example, although, in Embodiment 1, each of the blades are shaped such that the blade length continuously changes from the backing plate 11 toward the rim 13, each of the blades may have, in some part between the backing plate 11 and the rim 13, a portion in which the blade length is constant, that is, a portion in which the inside diameter ID is constant and that is not inclined relative to the rotation axis RS.
9
a: motor support, 10: impeller, 10C: impeller, 10D: impeller, 10E: impeller, 10F: impeller, 10G: impeller, 10H: impeller, 10e: air inlet, 11: backing plate, 11b: shaft portion, 12: blade, 12A: first blade, 12A1: first sirocco blade portion, 12A11: first sirocco region, 12A2: first turbo blade portion, 12A21: first turbo region, 12A21a: first turbo region, 12A2a: first turbo blade portion, 12A3: first radial blade portion, 12B: second blade, 12B1: second sirocco blade portion, 12B11: second sirocco region, 12B2: second turbo blade portion, 12B21: second turbo region, 12B21a: second turbo region, 12B2a: second turbo blade portion, 12B3: second radial blade portion, 12D: step portion, 12D1: side edge portion, 12D2: upper edge portion, 12R: outer circumferential region, 12t: end portion, 13: rim, 13a: first rim, 13b: second rim, 14A: inner circumferential end, 14A1: leading edge, 14B: inner circumferential end, 14B1: leading edge, 14H: leading edge, 15: heat exchanger, 15A: outer circumferential end, 15A1: trailing edge, 15B: outer circumferential end, 15B1: trailing edge, 16: case, 16a: upper surface portion, 16b: lower surface portion, 16c: side surface portion, 17: case discharge port, 18: case air inlet, 19: divider, 40: scroll casing, 41: scroll portion, 41a: scroll start portion, 41b: scroll end portion, 42: discharge portion, 42a: discharge port, 42b: extension plate, 42c: diffuser plate, 42d: first side plate portion, 42e: second side plate portion, 43: tongue, 44a: side wall, 44a1: first side wall, 44a2: second side wall, 44c: peripheral wall, 45: air inlet, 45a: first air inlet, 45b: second air inlet, 46: bellmouth, 46a: opening, 46b: inner peripheral end portion, 50: motor, 50A: motor, 50B: motor, 50a: end portion, 51: motor shaft, 52: outer peripheral wall, 52a: outer peripheral wall, 52b: outer peripheral wall, 71: first plane, 72: second plane, 100: multi-blade air-sending device, 100A: multi-blade air-sending device, 100B: multi-blade air-sending device, 100C: multi-blade air-sending device, 100D: multi-blade air-sending device, 100E: multi-blade air-sending device, 100F: multi-blade air-sending device, 100G: multi-blade air-sending device, 100H: multi-blade air-sending device, 112a: first blade portion, 112b: second blade portion, 122a: backing-plate-side blade region, 122b: rim-side blade region, 140: air-conditioning apparatus, 141A: inclined portion, 141A2: inclined portion, 141B: inclined portion, 141B2: inclined portion, 141C1: linear portion, 141C2: linear portion
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/JP2019/017548 | 4/25/2019 | WO |
| Publishing Document | Publishing Date | Country | Kind |
|---|---|---|---|
| WO2020/217367 | 10/29/2020 | WO | A |
| Number | Name | Date | Kind |
|---|---|---|---|
| 7186080 | Smiley, III | Mar 2007 | B2 |
| 20120269621 | Shirahama | Oct 2012 | A1 |
| 20160153457 | Jang et al. | Jun 2016 | A1 |
| Number | Date | Country |
|---|---|---|
| 101313153 | Nov 2008 | CN |
| 0 381 758 | Aug 1990 | EP |
| 0381758 | Aug 1990 | EP |
| 2000-240590 | Sep 2000 | JP |
| 2001-329994 | Nov 2001 | JP |
| 3516909 | Apr 2004 | JP |
| 2005-030349 | Feb 2005 | JP |
| 2005-069183 | Mar 2005 | JP |
| 2011-226410 | Nov 2011 | JP |
| 2020-503331 | Nov 2020 | JP |
| 10-1493267 | Mar 2015 | KR |
| WO-2019082378 | May 2019 | WO |
| 2020217367 | Oct 2020 | WO |
| Entry |
|---|
| Translation of EP0381758 (Year: 1990). |
| Translation of WO2019082378 (Year: 2019). |
| International Search Report dated Jul. 23, 2019, issued in corresponding International Application No. PCT/JP2019/017548 (and English Machine Translation). |
| Office Action dated Jun. 21, 2021, issued in corresponding JP Patent Application No. 2020-150970 (and English Machine Translation). |
| Office Action dated Feb. 12, 2020, issued in corresponding JP Patent Application No. 2020-503331 (and English Machine Translation). |
| Office Action dated Jun. 5, 2020, issued in corresponding JP Patent Application No. 2020-503331 (and English Machine Translation). |
| Extended European Search Report dated Mar. 22, 2022 issued in corresponding European Patent Application No. 19925853.4. |
| Examination Report dated May 5, 2022 issued in corresponding IN Patent Application No. 202127047699. (and English translation). |
| Office Action dated Apr. 22, 2023 issued in corresponding CN patent application No. 201980095561.5 (and English translation). |
| Number | Date | Country | |
|---|---|---|---|
| 20220145893 A1 | May 2022 | US |
