EP2264320B1 - Turbofan and air conditioner - Google Patents
Turbofan and air conditioner Download PDFInfo
- Publication number
- EP2264320B1 EP2264320B1 EP09731652.5A EP09731652A EP2264320B1 EP 2264320 B1 EP2264320 B1 EP 2264320B1 EP 09731652 A EP09731652 A EP 09731652A EP 2264320 B1 EP2264320 B1 EP 2264320B1
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- EP
- European Patent Office
- Prior art keywords
- blade
- side plate
- turbofan
- main plate
- circumferential surface
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000004378 air conditioning Methods 0.000 claims description 30
- 238000000926 separation method Methods 0.000 description 18
- 238000010586 diagram Methods 0.000 description 12
- 238000009826 distribution Methods 0.000 description 9
- 239000000428 dust Substances 0.000 description 8
- 230000009467 reduction Effects 0.000 description 8
- 230000000694 effects Effects 0.000 description 4
- 238000003466 welding Methods 0.000 description 4
- 238000013459 approach Methods 0.000 description 3
- 238000007664 blowing Methods 0.000 description 3
- 230000002093 peripheral effect Effects 0.000 description 3
- 229920005992 thermoplastic resin Polymers 0.000 description 3
- 238000009825 accumulation Methods 0.000 description 2
- 230000001154 acute effect Effects 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 239000012141 concentrate Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000000265 homogenisation Methods 0.000 description 2
- 238000005304 joining Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000002441 reversible effect Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000009751 slip forming Methods 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
- F04D29/282—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers the leading edge of each vane being substantially parallel to the rotation axis
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F1/00—Room units for air-conditioning, e.g. separate or self-contained units or units receiving primary air from a central station
- F24F1/0007—Indoor units, e.g. fan coil units
- F24F1/0018—Indoor units, e.g. fan coil units characterised by fans
- F24F1/0022—Centrifugal or radial fans
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F1/00—Room units for air-conditioning, e.g. separate or self-contained units or units receiving primary air from a central station
- F24F1/0007—Indoor units, e.g. fan coil units
- F24F1/0035—Indoor units, e.g. fan coil units characterised by introduction of outside air to the room
- F24F1/0038—Indoor units, e.g. fan coil units characterised by introduction of outside air to the room in combination with simultaneous exhaustion of inside air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F1/00—Room units for air-conditioning, e.g. separate or self-contained units or units receiving primary air from a central station
- F24F1/0007—Indoor units, e.g. fan coil units
- F24F1/0043—Indoor units, e.g. fan coil units characterised by mounting arrangements
- F24F1/0047—Indoor units, e.g. fan coil units characterised by mounting arrangements mounted in the ceiling or at the ceiling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F13/00—Details common to, or for air-conditioning, air-humidification, ventilation or use of air currents for screening
- F24F13/02—Ducting arrangements
- F24F13/06—Outlets for directing or distributing air into rooms or spaces, e.g. ceiling air diffuser
- F24F2013/0616—Outlets that have intake openings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Air-Conditioning Room Units, And Self-Contained Units In General (AREA)
Description
- The present invention relates to a turbofan and an air conditioning apparatus, and more particularly, to a turbofan for use in an air conditioning apparatus for air cleaning, humidifying, dehumidifying, cooling, or heating purposes and to an air conditioning apparatus provided with the same.
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- (A) A turbofan having a fan blade formed in a three-dimensional shape is widely used for a blower fan to be mounted on a conventional ceiling-embedded type air conditioning apparatus.
For example, there is disclosed a turbofan having a blade inlet diameter gradually increasing toward a side plate side from a main plate side, having an inlet diameter at a blade side plate inside end being greater than an inlet diameter of a side plate and having a blade upper end slanted in a rotational direction of an impeller, and a turbofan in which an inclination angle between the impeller rotational axis and the blade upper end is set at a greater angle at a position closer to the impeller outer circumference than to the impeller inner circumference, while the inclination angle is set at a smaller angle in the vicinity of the side plate, in a cross-sectional view as taken in the shape of a cylinder concentric with the impeller axis (seePatent Document 1, for example).
The turbofan according to this arrangement prevents an air flow from a blade upper end from separating on a blade negative-pressure surface as well as prevents degradation in air blowing performance and an increase in noise level due to turbulent flow. - (B) Also, as another conventional example, there is disclosed a turbofan in which the position of a side plate side jointed portion of a blade trailing edge is offset from a main plate side joined portion in an opposite impeller rotational direction by a predetermined distance, and at the same time the position of a side plate side jointed portion of a blade leading edge is offset from the main plate side joined portion in an impeller rotational direction by a predetermined distance (see
Patent Document 2, for example).
The turbofan according to this arrangement allows a blade pressure surface to be tilted toward the side plate side at the blade trailing edge, which causes a force exerted by the pressure surface on the air to lean against the side plate, preventing air flow separation on the outlet side of the side plate. In addition, it elongates a blade chord length on the blade side plate side having a greater flow speed at the blade leading edge, which causes the air flow entering to the blade leading edge near the main plate to head on the side plate side and prevents separated flow from occurring on the side of the outlet of the blade side plate, thereby homogenizing wind speed distribution on the front face side of the heat exchanger disposed downstream of the impeller in the entire vertical region. - (C) Furthermore, there are disclosed a turbofan having a joined end with the side plate shifted in the rotational direction in relation to a joined end with the main plate in a region from the leading edge to the trailing edge, and having the side plate end on the blade leading edge side slanted toward the rotational direction, a turbofan having the side plate end on the blade leading edge side slanted radially inward in the rotational direction with a greater inclination angle (inlet angle α) on the center side than on the main and side plate sides or a smaller inclination angle at on the side plate side than on the main plate side, and a turbofan having the side plate end at the blade trailing edge slanted radially outward in the opposite rotational direction with a greater inclination angle (outlet angle β) on the center side than on the main and side plate sides (see
Patent Document 3, for example). - The turbofans according to these arrangements cause the side plate side end of the blade leading edge having a particularly greater velocity component in the axial direction of inlet air to be slanted in the rotational direction so as to follow the air inlet direction, thereby securely preventing a separation forming readily in the opposite blade rotational direction and consequently providing improved performance and reduced noise levels. Also, a greater leading edge side inclination angle α at the center allows air to be very smoothly taken in from the inner circumferential side. Furthermore, if an inclination angle α on the side plate side is smaller than that on the main plate side, air can be smoothly taken in since the blade is shaped to follow the inlet angle. At the blade trailing edge, a greater inclination angle (outlet angle β) on the center side than on the main and side plate sides allows homogenization of air blown on the outer circumferential side.
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- [Patent Document 1] Japanese Unexamined Patent Application Publication No.
10-30590 page 4,Fig. 8 ) - [Patent Document 2] Japanese Patent No.
2701604 page 4,Fig. 3 ) - [Patent Document 3] Japanese Patent No.
3861008 Fig. 4 ) - However, a turbofan and an air conditioning apparatus disclosed in
Patent Documents 1 to 3 have the following problems. - (A) A turbofan disclosed in
Patent Document 1 has a difficulty in assembly. That is, at least in the case of a turbofan in which an impeller is integrally formed after molding a blade and a side plate separately and joining them into one unit by welding or fitting, if a blade upper end is slanted in the impeller rotational direction, such a slanted upper end causes a stress to be exerted on the main plate joined portion, so as to prevent a force from being properly applied to the side plate, because the side plate and the blade are joined by pressing the side plate on the blade in the direction of the rotational axis. - (B) In a case of forming of a thermoplastic resin, there is a problem of an increase in weight due to increasing amount of materials and poor workability. That is, forming of a thermoplastic resin may cause a surface sink, leading to poor workability. Since a thickness of a blade with poor workability is substantially equal along the impeller height direction from the main plate to the side plate, in a case of wing type blade in which the thickness of the blade gradually increases from the impeller inner circumference in a plan view perpendicular to the rotational axis and further decreases toward the impeller outer circumference, in the vicinity of the center of the blade having a larger thickness, for example, the thickness increases at the slanted blade upper edge in a side view resulting in increased amount of materials used, resultant increased weight, and occurrence of a surface sink.
- (C) In addition, an inclination angle at the blade upper edge is increased at lease toward the impeller outer circumference from the inner circumference so that the amount of inflow air at the blade side plate joined portion increases and as a result interferes with air flow from the blade impeller inner circumference of the blade, causing noise or vibration which degrades ambient surroundings (hereinafter called "degraded noise problem").
- (D) In a turbofan disclosed in
Patent Document 2, the side plate side joined portion of the blade trailing edge is offset by a predetermined amount in the opposite rotational direction from the main plate side joined portion, which improves the homogenization of wind speed distribution on the front face side of the heat exchanger disposed downstream of the impeller, but causes air flow to concentrate on the side plate side at the blade trailing edge in the impeller outlet, leading to a degraded noise problem. - (E) Offsetting the side plate side joined portion of the blade leading edge by a predetermined amount in the rotational direction from the main plate side joined portion prevents a separation around the side plate side joined portion, but a separation in a region from the intermediate portion of the blade leading edge to the blade side, plate side joined portion still remains unchanged, so that there is room for noise reduction.
- (F) Furthermore, the blade side plate side joined portion is slanted in the rational direction in relation to the main plate side joined portion, and the surface of the main plate and the blade pressure surface (surface of the opposite rotational direction) make a sharp angle of less than 90 degrees. This causes an inlet air flow from the leading edge to drift into the main plate side, leaving a separation region in the blade trailing edge at the side plate side.
- (G) In addition, offsetting the blade side plate side joined portion on the sides of the leading and trailing edges in the reverse direction causes a region from the blade side plate side joined portion joined to the side plate to the main plate side joined portion to be slanted relative to the side plate, which leads to a difficulty in assembly, like a turbofan disclosed in
Patent Document 1. - (H) Meanwhile, in a turbofan disclosed in
Patent Document 3, the side plate side joined portion is shifted over a portion from the blade leading edge to the trailing edge in the rotational direction in relation to the main plate side joined portion, and the side plate side end on the leading edge side is slanted in the rotational direction, which prevents separation of an inlet air flow at the side plate side end and the side plate side joined portion, but causes an inlet air flow from the leading edge to drift on the main plate side, leaving a separation region in the blade trailing edge on the side plate side. - (I) In the case of a turbofan formed by at least molding a blade and a side plate separately and joining them by welding or engagement into one unit, since the entire blade is slanted in the rotational direction, the blade and the side plate are joined with pressing the blade in the direction of the rotational axis, which causes a stress to be exerted on the main plate side joined portion and prevents a force from being properly applied to the blade on the side plate side, leading to a difficulty in assembly.
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JP 2008-2379 - The present invention has been achieved to solve the above described problems. An object of the present invention is to provide a turbofan and an air conditioning apparatus provided with the same, which provides low-noise emission, ease to assemble, and good workability by suppressing a separation region at a blade leading edge, a side plate side end, and a trailing edge, while minimizing performance degradation even if air flow resistance is added.
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- (1) According to the present invention, there is provided a turbofan as specified in the claims.
- (2) An air conditioning apparatus according to the present invention includes the turbofan mounted, and a ventilating pressure loss unit provided on the side of an inlet opening of the turbofan.
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- (i) With this arrangement, a turbofan according to the present invention provides a homogeneous wind speed distribution at the fan outlet opening. As a result, if a heat exchanger is provided downstream of the turbofan, air vertically uniformly flows in at least in the vicinity of the fan outlet opening, thereby suppressing an air flow that flows on the surface without passing through the heat exchanger due to a wind speed difference as well as reducing a pressure loss, resulting in a reduction in operating noise level.
- (ii) Also, an air conditioning apparatus according to the present invention suppresses air separation at a blade leading edge of the turbofan and provides low-noise operation, even if a ventilating pressure loss unit such as a filter is provided at a turbofan inlet opening.
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- [
Fig. 1] Fig. 1 is a longitudinal sectional view showing an air conditioning apparatus according toEmbodiment 1 of the present invention. - [
Fig. 2] Fig. 2 is a perspective view showing a turbofan according toEmbodiment 2 of the present invention. - [
Fig. 3] Fig. 3 is a plan view, partly in cross section, of a turbofan shown inFig. 2 , as viewed from a fan inlet opening side. - [
Fig. 4] Fig. 4 is a side view showing a section taken along the line X-X ofFig. 3 . - [
Fig. 5] Fig. 5 is a side view showing a blade of a turbofan shown inFig. 2 . - [
Fig. 6] Fig. 6 is a sectional view showing a section taken along the line L1-L1 ofFig. 5 . - [
Fig. 7] Fig. 7 is a sectional view showing a section taken along the line L2-L2 ofFig. 5 . - [
Fig. 8] Fig. 8 is a sectional view showing a section taken along the line L3-L3 ofFig. 5 . - [
Fig. 9] Fig. 9 is a sectional view showing a section taken along the line L4-L4 ofFig. 5 . - [
Fig. 10] Fig. 10 is a plan view showing a section taken along the line L5-L5 ofFig. 5 . - [
Fig. 11] Fig. 11 is a longitudinal sectional view showing a section taken along the line K1-K1 ofFig. 3 . - [
Fig. 12] Fig. 12 is a longitudinal sectional view showing a section taken along the line K2-K2 ofFig. 3 . - [
Fig. 13] Fig. 13 is a diagram showing relationship between a blade trailing edge inclination angle α and a noise level associated with the same air volume. - [
Fig. 14] Fig. 14 is a diagram showing relationship between a circumferential curvature angle γ and a noise level associated with the same air volume. - [
Fig. 15] Fig. 15 is a diagram showing relationship between an outlet angular difference Δβ2 and a noise level associated with the same air volume. - [
Fig. 16] Fig. 16 is a diagram showing relationship between a curvature angle ε and a noise level associated with the same air volume. - [
Fig. 17] Fig. 17 is a diagram showing relationship between an inlet angular difference Δβ1 and a noise level associated with the same air volume. - [
Fig. 18] Fig. 18 is a perspective view showing a turbofan according toEmbodiment 3 of the present invention. - [
Fig. 19] Fig. 19 is a longitudinal sectional view of a blade of a turbofan shown inFig. 18 . -
Fig. 1 is a longitudinal sectional view showing an air conditioning apparatus according toEmbodiment 1 of the present invention. An air conditioning apparatus according toEmbodiment 1 of the present invention is equipped with a turbofan according toEmbodiment 2 to be described later, and is described below with reference to accompanying drawings. - In
Fig. 1 , a ceiling-embedded type air conditioning apparatus body (hereinafter referred to as "air conditioning apparatus body") 10 is mounted on aceiling 21 of aroom 20 in such a manner that it is embedded in a rectangular-shaped hole formed in theceiling 21. In other words, the air conditioning apparatus body is a box having an opening formed at the bottom thereof and having atop plate 10a and aside plate 10b opposed to thetop plate 10a. Theside plate 10b has a side plate opening (communicating with a body inlet opening 10c) formed at the center thereof and has a bottom edge substantially flush with theceiling 21, so an opening of the air conditioning apparatus body is also substantially flush with theceiling 21. - In addition,
decorative panel 11 shaped substantially in a rectangle in a plan view is installed on theside plate 10b or theceiling 20 while facing theroom 20 so as to cover the lower end of theside plate 10b and the rectangular-shaped hole of theceiling 21. Thedecorative panel 11 includes aninlet grill 11a, which is an inlet opening of air for the airconditioning apparatus body 10, provided at the center thereof, afilter 12 for removing dust from the air having passed through theinlet grill 11a, a panel outlet opening 11b formed along each side of thedecorative panel 11. Eachpanel outlet opening 11b is provided with awind direction vane 13. - Furthermore, inside the air
conditioning apparatus body 10 aturbofan 1, abell mouth 14 that forms an inlet air passage for the turbofan, afan motor 15 for turning and driving theturbofan 1, and aheat exchanger 16 for performing heat exchange of room air drawn into the apparatus body (hereinafter referred to as "drawn air") are disposed respectively. Theheat exchanger 16 is formed to have a substantial C-shaped form in the plan view , installed uprightly so as to surround the periphery of theturbofan 1, and connected to an outdoor unit (not illustrated) through connecting piping. - The air
conditioning apparatus body 10 includes a body inlet opening 10c formed at the center thereof, and a body outlet opening 10d is formed around the body inlet opening 10c. The body inlet opening 10c communicates with theinlet grill 11a of the facingpanel 11, while the body outlet opening 10d communicates with the panel outlet opening 11b of thedecorative panel 11. - In the
air conditioning apparatus 10 according to this arrangement, when theturbofan 1 rotates, the air in theroom 20 is drawn into theturbofan 1 after passing through theinlet grill 11a of thedecorative panel 11, thefilter 12 removing dust, the body inlet opening 10c, and thebell mouth 14. Then, the air blows off into theheat exchanger 16 where the air is subjected to heat exchanging including heating or cooling and dehumidifying, and is blown out from the panel outlet opening 11b toward theroom 20 through the body outlet opening 10d while subjected to wind direction control by thewind direction vane 13. Whereby, the air in theroom 20 is air-conditioned (hereinafter referred to as "air conditioning"). -
Figs. 2 through 17 are views showing a turbofan according toEmbodiment 2 of the present invention.Fig. 2 is a perspective view.Fig. 3 is a plan view, partly in cross section, of a turbofan, as viewed from a fan inlet opening side.Fig. 4 a side view showing a section taken along the line X-X ofFig. 3 .Fig. 5 is a partial side view.Figs. 6 through 9 are partial planar sectional views.Fig. 10 is a partial plan view.Figs. 11 and12 are partial sectional views.Figs. 13 through 17 are diagrams showing the relationship between a noise level and an angle of each section. -
Fig. 2 corresponds to a perspective view ofFig. 1 , as seen when looking up at theceiling 21.Fig. 4 andFig. 1 (Embodiment 1) are upside-down views, where air is drawn from the upper side inFig. 4 and blown off toward the right and left directions inFig. 4 . A top to bottom direction inFig. 4 is called "height direction", while a left to right direction and a face-to-back direction is called "horizontal direction" for convenience sake. InFig. 1 and the other figures, the same reference numbers and symbols refer to the same components, and descriptions of the components are partially omitted. -
Fig. 13 is a diagram showing relationship between a blade trailing edge inclination angle α and a noise level associated with the same air volume.Fig. 14 is a diagram showing relationship between a circumferential curvature angle γ and a noise level associated with the same air volume.Fig. 15 is a diagram showing relationship between an outlet angular difference Δβ2 and a noise level associated with the same air volume.Fig. 16 is a diagram showing relationship between a curvature angle ε at a blade leading edge end 4a3 and a noise level associated with the same air volume in relation to the ratio of an air flow resistance without dust accumulation on a filter disposed at an inlet side to that with dust accumulation.Fig. 17 is a diagram showing relationship between an inlet angular difference Δβ1 and a noise level associated with the same air volume, the inlet angular difference being an angular difference between an inlet angle the blade leading edge end and an inlet angle at a blade leading edge inner circumferential side end at a height of a concave-shaped bottom where a vertical camber line C12 becomes most along the opposite rotational direction in a blade outer circumferential surface. - In
Figs. 2 through 5 , theturbofan 1 is integrally formed of amain plate 2 of a body of revolution (disk) having a substantially angular-shaped section, aside plate 3 of a circular ring having a substantially circular arc section disposed so as to be opposed to the periphery of themain plate 2, and a plurality ofblades 4 disposed so as to extended from themain plate 2 to theside plate 3. Themain plate 2 includes aboss 2a formed at the center (convex portion having a substantially angular shaped section) thereof, theboss 2a being a fixing part to which arotational shaft 0 of thefan motor 15 is secured. Accordingly, a rotational axis is parallel to the height direction and perpendicular to the horizontal direction. - In the
side plate 3 in the form of a circular ring, a side plate opening formed at the center thereof forms afun inlet opening 1a. The peripheral portion (skirt having a substantially angular shaped section) of themain plate 2 and theside plate 3 form wind guide walls, and a space defined by these components forms afan outlet opening 1b. In other words, inFig. 1 , since the section of the peripheral edge of themain plate 2 and the section of theside plate 3 are rising toward the outer circumference, air flow is formed which rises (indicated by a downward arrow since the upside is down inFigs. 2 through 12 ) and then horizontally moves toward the outer circumference. - In a plan view of the
blade 4, theblade 4 is located farther away from the rotational axis O as it comes nearer to the blade trailing edge from theblade leading edge 4a. The blade is connected at its end edge of theblade 4 close to theside plate 3 to the side plate in a region (4ec4∼4g1) close to theblade trailing edge 4e, and is located at the side plate opening away from theside plate 3 in a region (4g1∼4a3) close to theblade leading edge 4a. Theblade 4 has a hollow structure having a cavity therein and an opening formed outside of the impeller of themain plate 2 in such a manner that a wall thickness T (equal to the distance between the blade outer circumferential surface and the blade inner circumferential surface) in a horizontal section perpendicular to the rotational axis O of theblade 4 decreases from a position close to themain plate 2 toward a position close to theside plate 3. - The
blade trailing edge 4e of theblade 4 is located on a hypothetical cylinder defined by connecting the circumferential edges of themain plate 2 and theside plate 3, and has a wavy form having at least two inflection points on such a hypothetical cylinder. Namely, an intersection of a horizontal camber line C1 and theblade trailing edge 4e depicts, in relation to an intersection 4ec1 as a main plate side joined point in the height direction, an intersection 4ec2 which is a main plate side inflection point having a curvature toward a rotational direction in a convex form at a predetermined position on the side of themain plate 2 closer to the center of thefan outlet opening 1b, an intersection 4ec3 which is a side plate side inflection point having a curvature toward the reverse rotational direction in a concave form on the side of theside plate 3 closer to the center of thefan outlet opening 1b, and an intersection 4ec4 which is a side plate side joined point of theside plate 3. In other words, a line G connecting between the main plate side joined portion 4ec1 and the side plate side joined portion 4ec4 is upright in the vicinity of themain plate 2 and theside plate 3 so as to be parallel to the rotational axis O, while the blade trailing edge on the side of themain plate 2 is inclined to the rotational direction A in relation to that on the side of theside plate 3 between the main plate side inflection point 4ec2 and the side plate side inflection point 4ec3 so that theblade trailing edge 4e has a substantial S shape. - At this time, the
blade trailing edge 4e is located on a hypothetical cylinder defined by connecting the outer circumferential edges of themain plate 2 and theside plate 3, and a line G connecting a main plate side jointed point 4ec1 and a side plate side joined point 4ec4 is orthogonal (orthogonal as a normal line) to the outer circumferential surface of themain plate 2 so as to be parallel to the rotational axis O. - Also, the
blade trailing edge 4e is parallel to the normal line of theside plate 3 in the vicinity of theside plate 3. Furthermore, between main plate side curvature point 4ec2, which is a location in a main plate side curved portion most projected to the rotational direction A, and the side plate side curvature point 4ec3, which is a location in a side plate side curved portion most projected to the opposite direction of the rotational direction A, theblade trailing edge 4e projects more to the rotational direction A as it is closer to themain plate 2, so as to be inclined in a side view. As a result, theblade trailing edge 4e has a substantial S shape. - Accordingly, on the blade outer
circumferential surface 4b, drawn air is divided by the main plate side curvature point 4ec2 into the sides of themain plate 2 and the central part in the height direction of theoutlet opening 1b, thereby preventing air flow from concentrating on the side of themain plate 2. An inclined section 4e5 between the main plate side curvature point 4ec2 and the side plate side curvature point 4ec3 exerts a force in the direction of theside plate 3, guiding the air flow. In addition, a portion between the side plate side curvature point 4ec3 and the side plate side joined point 4ec4 guides, on the blade innercircumferential surface 4c thereof, air flow coming from a portion around the side plate side joinedportion 4g at the leading edge side plate side end 4a1 of theblade 4 to the side of theside plate 3 in thefan outlet opening 1b. - The horizontal cross-sectional shape of the
blade 4 will be described.Figs. 6 through 10 are sectional views taken along the line L1-L1, the line L2-L2, the line L3-L3, the line L4-L4, and the line L5-L5 ofFig. 4 , respectively. The rotational direction is indicated by "Arrow A". - In other words,
Fig. 6 is a sectional-view taken along the line L1-L1 at the mainplate side end 4d joined to themain plate 2.Fig. 7 is a cross-sectional view taken along the line L2-L2 located on the side of themain plate 2 from the center of thefan outlet opening 1b.Fig. 8 is a cross-sectional view taken along the line L3-L3 located on the side of theside plate 3 from the center of thefan outlet opening 1b.Fig. 9 is a cross-sectional view taken along the line L4-L4 going through theside plate 3 in thefan outlet opening 1b.Fig. 10 is a cross-sectional view taken along the line L5-L5 when removing theside plate 3 corresponding to oneblade 4. - In the L1-L1 section (
Fig. 6 ), a wall thickness center line (equal to the center between the blade inner and outer circumferential surfaces) in the section is indicated by "horizontal camber line C1", and "the intersection of the horizontal camber line C1 and theblade leading edge 4a" and "the intersection of the horizontal camber line C1 and theblade trailing edge 4e" are indicated by "4ac1" and "4ec1", respectively. - Also, in the L2-L2 section (
Fig. 7 ), a wall thickness center line in the section is indicated by "horizontal camber line C2", and "the intersection of the horizontal camber line C2 and theblade leading edge 4a" and "the intersection of the horizontal camber line C2 and theblade trailing edge 4e" are indicated by "4ac2" and "4ec2", respectively. - Likewise, in the L3-L3 section (
Fig. 8 ), "horizontal camber line C3" is indicated by "4ac3" and "4ec3". Also, in the L4-L4 section (Fig. 9 ), "horizontal camber line C3" is indicated by "4ac4" and "4ec4". Reference numerals "4ac1" and "4ec1" are added to each figure to make clear a phase in the height direction. - In
Figs. 6 through 9 , theblade 4 is an wing type blade which is gradually thickening toward the center of the blade from the blade inner circumference side leading edge 4a2, and is gradually thinning toward theblade trailing edge 4e. - In an L1-L1 section shown in
Fig. 6 , theblade 4 is slanted backward against the rotational direction A and radially outwardly curved. In a section L2-L2 shown inFig. 7 , the side of themain plate 2 of theblade trailing edge 4e is curved in a warped backward shape in the rotational direction A. In addition, in an L3-L3 section shown inFig. 8 , theblade trailing edge 4e is curved in a warped shape in the direction opposite to the rotational direction A against the main plate side joined part 4ec1. - IN the L4-L4 section shown in
Fig. 9 , the side plate side jointed point 4ec4 and the main plate side joined point 4ec1 in the L1-L1 section shown inFig. 6 have the same phase in a plan view as seen from the fan inlet opening la, and the leading edge inner circumference side end radially outwardly curves. - In addition, in a plan view shown in
Fig. 10 , the main plate side curvature point 4ec2 and the side plate side curvature point 4ec3 are disposed so as to make a predetermined angle γ across the main plate side joined point 4ec1 and the side plate side joined point 4ec4. - In
Fig. 6 (L1-L1 section), the angle (acute angle) between a tangent line E1 to the horizontal camber line C1 at the intersection 4ec1 of the horizontal camber line C1 and theblade trailing edge 4e, and a tangent line F1 to a circle concentric with the rotational axis O and passing through the intersection 4ec1 is referred to as "outlet angle β21". - In
Fig. 7 (L2-L21 section), the angle (acute angle) between a tangent line E2 to the horizontal camber line C2 at the intersection 4ec2 of the horizontal camber line C2 and theblade trailing edge 4e, and a tangent line F2 to a circle concentric with the rotational axis O and passing through the intersection 4ec2 is referred to as "outlet angle β22". Likewise, "outlet angle β23" and "outlet angle β24" are defined inFig. 8 (L3-L3 section) andFig. 9 (L4-L4 section), respectively. - The
blade 4 is formed such that these outlet angles have the relationship of "β23 < β21 = β24 < β22". - In
Figs. 2 and3 , theblade leading edge 4a on theblade 4 at the air inlet side has a shape defined by the side plate side end 4a1 and the inner circumferential side end 4a2 continuously formed with the leading-edge end 4a3 as a bending point. The side plate side end 4a1 is tilted toward thefan inlet opening 1a as it approaches "side plate joinedportion 4g (seeFig. 4 ) where theblade 4 and theside plate 3 are joined" from the leading-edge end 4a3. In other words, the side plate side end 4a1 approaches theside plate 3 being inclined so as to approach the normal line of theside plate 4. - In
Fig. 3 , the intersection of the horizontal camber line C1 and the blade leading edge inner circumferential side end 4a2 is called "intersection 4ac1", the intersection of the horizontal camber line C1 and the blade trailingedge end 4e is called "intersection 4ec1", and a line connecting the intersection 4ac1 and the intersection 4ec1 is called "chord line D". - A longitudinal section perpendicular to the chord line D in the vicinity of the blade leading edge inner circumferential end 4a2 is called "K1-K1 section", and the
blade 4 in the K1-K1 section is shown inFig. 11 . A longitudinal section perpendicular to the chord line D at the end in a rotational direction 4g1 of the side plate joined portion (equal to the boundary between a joined region and a region located at the side plate opening) is called "K2-K2 section", and theblade 4 in the K2-K2 section is shown inFig. 12 . - In
Figs. 11 and12 , vertical thickness center lines (equal to the center line between the blade inner circumferential surface and the blade outer circumferential surface) in the K1-K1 section and the K2-K2 section are called "vertical camber lines C12", while angles between the vertical camber line C12 and the rotational axis O at the blade leading edge end 4a3 (K1-K1 section) and at the blade side plate joined portion 4g1 (K2-K2 section) are called "curvature angle ε1" and curvature angle ε2", respectively. - In
Figs. 2 ,11 , and12 , a region apart from theside plate 3, in an end edge of the blade close to the side plate 3 (equal to the region located at the side plate opening), curves so as to be located more radially outward at a position closer to theblade leading edge 4a in a plan view, and expands so as to be farther away from the end edge at the curved region closer to theblade leading edge 4a in a side view. - In other words, the blade leading edge side plate side end 4a1 and the leading edge inner circumferential side end 4a2 on the side of the
side plate 3 curves radially outward so that the curvature angle ε becomes larger at a position closer to the impeller inner circumference (equal to a position closer to theblade leading edge 4a) with the end in the rotational direction 4g1 on the blade outer circumferential surface of the side plate joinedportion 4g being as a supporting point and the blade leading edge end 4a3 being as a power point. - Consequently, the curved region is formed to have a substantial triangle shape in a side view, causing an oblique "folding line B" to be created on the outer
circumferential surface 4b of theblade 4 so as to extend toward the blade leading edge inner circumferential side end 4a2 of the blade leading edge from the end in the rotational direction 4g1 to themain plate 2. - In addition, as shown in
Figs. 4 and11 , the blade thickness T is made gradually larger so that the blade outercircumferential surface 4b of theblade leading edge 4a on the side of themain plate 2 curves radially outward, and at the same time the vertical camber line C12 curves radially outward. - In the K2-K2 section shown in
Fig. 12 , the blade outercircumferential surface 4b is substantially perpendicular to the outer circumferential surface of themain plate 2. Only the blade innercircumferential surface 4c on the side of theside plate 3 curves radially outward, and theblade 4 stands substantially upright with its thickness becoming smaller toward theside plate 3 from the main plate 2(with increasing height), as a whole. - For inlet angles β11, β12, β13, and β14 shown in cross-sectional views of
Figs. 6 through 10 , an inlet angle β1 gradually becomes larger in a region from the blade leading edge end 4a3 to theside plate 3 to cause the inlet angle β14 at the blade leading edge end 4a3 to be the smallest, so that β14 is smaller than β11, and β12 and β13 of middle portions in the height direction are greater than at least β11 and β14, respectively (β12>β11, β13>β14). - As described above, in a side view as seen from the inner circumference, the
blade leading edge 4a is at least so formed that the blade outercircumferential surface 4b on the sides of the blade side plate 4a1 and themain plate 2 is formed to have a convex shape in relation to the rotational direction A, while the blade innercircumferential surface 4c is formed so as to curve radially outward. - As shown in
Fig. 2 , when being rotated by thefan motor 15 in the rotational direction A, theturbofan 1 having the above structure substantially radially blows out the room air (drawn air), which has been drawn through thefan inlet opening 1a and passed through theblade 4, through thefan outlet opening 1b, providing the following effects and advantages. -
- (i) A homogeneous wind speed distribution is provided at the
fan outlet opening 1b. As a result, if theheat exchanger 16 is provided downstream of theturbofan 1, the air flows uniformly into the heat exchanger, at least in the vicinity of thefan outlet opening 1b, thereby suppressing a secondary air flow that flows on the surface without passing through theheat exchanger 16 due to a wind speed difference as well as reducing a pressure loss, resulting in a reduction in operating noise level (seeFig. 1 ).
Also, theblade trailing edge 4e stands upright in the vicinity of themain plate 2 and theside plate 3, which allows a force parallel to the rotational axis O to be precisely applied at the time of welding work during assembly, as compared with conventional turbofans where the trailingedge 4e is inclined in relation to themain plate 2 and theside plate 3, thereby preventing defective welding caused by the back clearance of theblade 4. - (ii) "Trailing edge inclination angle α2" or an inclination angle between an inclined section 4e5, which is located between the main plate side curvature point 4ec2 and the side plate side curvature point 4ec3, and a line G parallel to the rotational axis O is set at 10 to 30 degrees. This prevents a flow from concentrating on the blade outer
circumferential surface 4b on the side of theside plate 3 in thefan outlet opening 1b. Also, this prevents a flow coming from the leading edge side plate side end 4a1 from concentrating on the blade innercircumferential surface 4c on the side of theside plate 3, thereby reducing a noise level as shown in the relationship between the trailing edge inclination angle α and the noise level associated with the same wind volume (seeFig. 13 ). - (iii) In
Fig. 10 , a circumferential curvature angle γ between a line connecting the impeller rotational axis with the main plate side curvature point 4ec2 and a line connecting the rotational axis with the side plate side curvature point 4ec3 is set at 5 to 15 degrees. When theheat exchanger 16 is disposed downstream of thefan outlet opening 1b, this arrangement allows the air flow to be dispersed even at the time when theblade trailing edge 4e becomes close to theheat exchanger 16 due to runningturbofan 1 and an air flow resistance increases locally. Like the effects of the trailing edge inclination angle α, this arrangement also prevents a flow from concentrating on the side of theside plate 3 of the blade outercircumferential surface 4b in thefan outlet opening 1b, as well as prevents a flow coming from the leading edge side plate side 4a1 from concentrating on the side of theside plate 3 of the blade innercircumferential surface 4c, thereby reducing a noise level as shown in the relationship between the circumferential curvature angle γ and the noise level associated with the same wind volume (seeFig. 14 ). - (iv) In each cross sectional view of the blade in a plane perpendicular to the rotational axis, "angular difference Δβ2" that is a difference between the outlet angle β22 at the main plate side curvature point 4ec2 and the outlet angle β23 at the side plate side curvature point 4ec3 is set at 20 to 35 degrees. Accordingly, in the
air conditioning apparatus 10, the blade trailing edge is formed to have a substantial S shape with concave and convex curvature, so that even if a distance between the heat exchanger 16 (ventilating pressure-loss body having a substantial C shape in a plan view) disposed on the fan outlet side and the fan outlet opening 1b changes in the circumferential direction, theblade trailing edge 4e regulates an air flow due to the substantial S-shape.
Consequently, the present invention provides a small change in wind speed distribution, thereby reducing a noise level, unlike conventional apparatuses in which an air flow concentrates on thefan outlet opening 1b on the side of themain plate 2, in a region where thefan 1 is close to theheat exchanger 16, which causes a greater separation on the side of theside plate 3 and a significant increase in noise level (seeFig. 15 showing the relationship between an outlet angular difference Δβ2 and a noise level associated with the same air volume). - (v) On the
blade leading edge 4a, drawn air is smoothly introduced without hitting the outercircumferential surface 4b and producing a turbulent flow at the blade leading edge inner circumferential side end 4a2 on the side of theside plate 2 and at the side plate side induction portion 4b1 (leading edge side plate side end 4a1 curves radially outward) on the blade outercircumferential surface 4b, since, in a side view as seen from the center (rotational axis O), the outercircumferential surface 4b on the side of theside plate 3 and themain plate 2 curves to have a concave shape in relation to the rotational direction A.
This arrangement increases a blowing air volume at the same fan rotating speed, leading to a lower fan rotating speed than that for attaining the blowing air volume required for heat exchange of theair conditioning apparatus 10, which results in reduced operating noise levels as well as reduced motor power consumption due to performing a rotational drive of the fan with a reduced driving torque. - (vi) The blade outer
circumferential surface 4b of theblade leading edge 4a on the side of themain plate 2 is formed to curve radially outward, which allows an air flow passing through the surface of themain plate 2 from theboss 2a to be directed toward the center of the blade height, preventing the air flow from concentrating on the side of themain plate 2, together with an air flow from the blade leading edge inner circumferential side end 4a2.
Also, the air flow can be smoothly introduced to the blade outercircumferential surface 4b without hitting theblade 4, thereby preventing turbulence.
Consequently, a homogeneous blown off wind speed distribution as well as reduced noise levels can be achieved by preventing a separation on the side plate side and a concentration on the main plate side, while conventional apparatuses suffer from the concentration of wind speed distribution on the main plate side in the fan outlet opening. - (vii) The blade inner
circumferential surface 4c of theblade leading edge 4a on the side of theside plate 3 is formed to be slanted radially outward and curved, which allows drawn air on the innercircumferential surface 4c to smoothly flow along the slanted, curved surface toward theblade trailing edge 4e. This prevents the air flow separation occurring near theside plate 3 that is encountered in conventional turbofans, thereby reducing noise levels. - (viii) With the end in the rotational direction 4g1 on the blade
circumferential surface 4b at the side plate joinedportion 4g being as a supporting point and the blade leading edge end 4a3 being as a power point, the "curvature angle ε(equal to an angle between the vertical camber line C12 and the a line parallel to the rotational axis O) becomes larger toward the inner circumference side of the impeller in a longitudinal cross section perpendicular to the chord D in a horizontal section at the blade mainplate side end 4d. In other words, the leading edge side plate side end 4a1 and the leading edge inner circumferential side end 4a2 on the side of theside plate 3 curves radially outward toward therotational direction surface 4b of the blade 4 (toward the blade leading edge inner circumferential side end 4a2 from the inner circumferential side end 4g1 of the side plate joined portion) so as to create a folding line B (oblique line, seeFig. 2 ) going toward themain plate 2 side.
This arrangement reduces the difference between an inflow at the blade leading edge inner circumferential side end 4a2 on the side of theside plate 3 and an inflow at the leading edge side plate side end 4a1, as compared with a conventional curvature with starting point on the horizontal line perpendicular to the rotational axis O. - (ix) The leading edge inner circumferential side end 4a2, and the leading edge side plate side end 4a1 are connectively formed into a substantially triangle shape with the leading edge end 4a3 as an apex, which homogenizes a vertical vortex occurring at the blade leading edge inner circumferential side end 4a2 and the leading edge side plate side end 4a1 around the blade leading edge end 4a3, causing to be stabilized by an air flow to be guided onto the blade inner
circumferential surface 4c. Accordingly, even if the filter 12 (ventilating, pressure loss body disposed on the side of thefan inlet opening 1a) has dust built up thereon and air flow resistance is increased, air flow separation can hardly occurs, thereby suppressing noise levels deterioration to be low. - (x)
Fig. 16 is a diagram showing the relationship between a curvature angle ε and "noise level in relation to air flow resistance ratio" associated with the same air volume. Namely, it shows "noise level in relation to air flow resistance ratio" that is the ratio of a value for the filter having no dust buildup to that for the filter having a dust buildup. As shown inFig. 16 , if ε1 falls within a range between 25 and 45 degrees, a low-noise turbofan and a low-noise air conditioning apparatus which hardly suffers from air flow separation regardless of a change in air flow resistance at thefan inlet opening 1a can be obtained. - (xi) In addition, as shown in
Fig. 12 , theblade 4 has its thickness T decreasing toward theside plate 3 in the height direction of the fan from themain plate 2 and has a hollow structure having anopening 2b on the outside of the impeller of themain plate 2, which contributes to a reduction in weight. This arrangement reduces starting torque exerted on theboss 2a at a start of a fan motor as well as suppresses distortion, leading to an improvement in durability of theturbofan 1. - (xii) Furthermore, in the
blade 4, the longitudinal cross section K1-K1 shown inFig. 6 (longitudinal cross section containing the end in the rotational direction 4g1 in the side plate joined portion of theblade 4 perpendicular to the chord D in a horizontal cross section at the blade mainplate side end 4d) and a predetermined region toward the downstreamblade trailing edge 4e are formed so as to substantially stand upright in parallel to the rotational axis O in relation to themain plate 2. Consequently, when themain plate 2 is pressed against theblade 4 in parallel to the rotational axis O in order to weld theblade 4 and theside plate 2 into one body, "stress concentration at the blade mainplate side end 4d" to be encountered by a conventional blade being slanted relative to themain plate 2 can be mitigated, thereby preventing the buckling of theblade 4 so as to lead to the facilitation of assembly as well as improved reliability. - (xiii) As to an inlet angle β1 in each cross-sectional view of the
blade 4 taken along a plane perpendicular to the rotational axis O, the inlet angle β14 at the blade leading edge end 4a3 is the smallest in theleading edge 4a. In addition, the inlet angle β1 at a portion close to the center in the impeller height direction in the blade leading edge inner circumferential end 4a2, is formed radially inward so as to be greater than the inlet angle β11 on the main plate side and the inlet angle β14 at the blade leading end, that is, it has a relationship of β1 > β11 > β14.
In addition, the inlet angle β1 is designed to gradually become larger toward the side plate joinedportion 4g from the blade leading edge end 4a3 in the blade side plate side end 4a1, thereby reducing "an incident angle δ" which is the angular difference between "inlet flow J" and the inlet angle β1 on a horizontal section perpendicular to the rotational axis O at the blade leading edge inner circumferential side end 4a2, as well as allowing drawn air to be smoothly drawn in with less separation, which leads to a reduction in noise levels. - (xiv) From the blade leading edge end 4a3 to the side plate joined
portion 4g in the blade leading edge side plate side end 4a1, the drawn air is radially introduced with a slope toward thefan inlet opening 1a, and further radially introduced by gradually increasing the inlet angle β, so as to mitigate the separation on the side of theside plate 3 as well as to homogenize the wind speed distribution in thefan outlet opening 1b. - (xv) An angular difference between the inlet angle β14 (see
Figs. 8 and11 ) at the blade leading edge end 4a3 and the inlet angle β12 at the leading edge inner circumferential side end 4a2 (seeFigs. 7 and11 ) at a height position on a concave-shaped bottom in which the vertical camber line C12 is most directed in the opposite rotational direction on the blade outercircumferential surface 4b is set as "angular difference Δβ1".
With this arrangement, as shown inFig. 17 , although excessively greater angular difference Δβ1 causes a separation on the blade innercircumferential surface 4c on the side of themain plate 2 as well as increased noise levels, the angular difference Δβ1 of 10 to 20 degrees causes a reduction in noise levels. - (xvi) Incidentally, a
blade trailing edge 4e formed into a curved shape as substantial S shape and ablade leading edge 4a formed to curve radially outward provide noise reduction effects individually, as compared with the conventional blade. - In addition, the combination of these shapes allows the drawn air to be smoothly drawn in along the entire
blade leading edge 4a, causing a rectified air flow to be drawn in toward theblade trailing edge 4e. This facilitates the flow of the drawn air along the substantial S shaped surface of the blade with less turbulence, further homogenizing the wind speed distribution and reducing noise levels by synergistic effect. - As described above, a turbofan according to the present invention is a low-noise, reliable, and durable turbofan. An air conditioning apparatus provided with such a turbofan ensures a comfortable usage environment free from harsh noise as well as a trouble free use for a long time. Thus, a low-cost, high-quality air conditioning apparatus can be provided.
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Figs. 18 and19 show a turbofan according toEmbodiment 3 of the present invention.Fig. 18 is a perspective view, whileFig. 19 is a partial cross-sectional view (to be precise, a longitudinal sectional view of theblade 4 in a plane perpendicular to the chord D at the blade mainplate side end 4b). The same symbols and reference numerals inFigs. 18 and19 as those in Embodiment 2 (Figs. 2 through 12 ) refer to the same components, and repeated descriptions of the same components are partially omitted. - In
Fig. 18 , a leading edge side plate side end 4a1 which is an edge of theblade 4 close to theside plate 3 curved so as to be placed more radially outward as it becomes closer to the leading edge inner circumferential side end 4a2 in a plan view, in a region away from the side plate 3 (equal to a region located at the side plate opening), and the curved region expands so as to become away from that end as it becomes closer to the leading edge inner circumferential side end 4a2 in a side view. - In other words, the
turbofan 30 has a folding line B heading gradually in the direction of themain plate 2, which is formed in the radially outward curving leading edge side plate side end 4a1 of theblade 4 and in the blade outercircumferential surface 4b at the leading edge inner circumferential side end 4a2 on the side of theside plate 3 so as to be directed toward the leading edge inner circumferential side end 4a2 of theblade 4 from the end in the rotational direction 4g1 in the blade outercircumferential surface 4b at the side plate joinedportion 4g. - In addition, a rectangular-shaped
concave groove 5 is formed in the blade innercircumferential surface 4c in the curved region so as to be substantially perpendicular to the folding line B and obliquely outwardly extend to the side of themain plate 2 from the side of theside plate 3 in relation to the rotational axis O. - In
Fig. 19 , theconcave groove 5 becomes shallower as it is closer to the leading edge side plate side end 4a1. - In other words, the
blade 4 is formed of a component constituting the blade outer circumferential surface and a component constituting the blade inner circumferential surface, and has a dual structure having a hollow formed therein. These two components are joined together at the leading edge side plate side end 4a1, and the distance between them becomes larger at a position further away from the leading edge side plate side end 4a1. - The
groove bottom 5a of theconcave groove 5 is formed with the component constituting the blade outer circumferential surface, so the depth of theconcave groove 5 corresponds to the distance between the inner circumferential surface of the component constituting the blade outer circumferential surface and the inner circumferential surface of the component constituting the blade inner circumferential surface. - When driven by a fan motor in the rotational direction A, the
turbofan 30 having the above structure draws air through thefan inlet opening 1a and substantially radially blows out the drawn air in the rotational direction through thefan outlet opening 1b, after passing through theblade 4. - When air is drawn into the
blade 4, the air smoothly flows on and along the blade outercircumferential surface 4c to the blade trailing edge without any turbulence, since the leading edge side plate side end 4a1 curves in the radially outward direction. Also, theconcave groove 5 extends obliquely so as to expand toward the side of themain plate 2 from the side of theside plate 3 in relation to the rotational axis O, thereby allowing thegroove bottom 5a to rectify the air flow and suppress the turbulence, leading to further reduction in noise levels. - The
groove bottom 5a of theconcave groove 5 is formed to extend along the blade outercircumferential surface 4b, so as to make the thickness of theblade 4 smaller. In the case of a turbofan formed of a thermoplastic resin, this arrangement prevents a surface sink due to smaller wall thickness even at a curved portion which tends to have a larger wall thickness, resulting in improved reliability in forming. - In particular, the
turbofan 30, if installed on an air conditioning apparatus 10 (seeFig. 1 ) having a ventilating pressure loss body such as a filter disposed at the fan inlet opening 1a thereof, prevents an air flow separation and maintains low noise levels even if dust gradually accumulates on the filter and results in increased air flow resistance. - A turbofan according to the present invention can be widely used for household use and industrial use due to its low-noise and high manufacturing reliability. In addition, such a turbofan can be widely used in home-use and industrial air conditioning apparatuses.
Claims (15)
- A turbofan comprising:a disc-shaped main plate (2) having a boss (2a) that is a fixed portion to which a rotational shaft (O) of a motor is secured;an annular side plate (3) having a side plate opening formed at the center thereof and forming a wind guide wall together with the main plate (2); anda plurality of blades (4) mounted so as to extend between the main plate (2) and the side plate (3);in a plan view of the blade (4), each blade (4) being positioned farther away from the rotational shaft (O), when coming from a blade leading edge (4a) to a blade trailing edge (4e); wherein an outer circumferential surface (4b) and an inner circumferential surface (4c) of the blade (4) at the blade leading edge (4a) have a central region in the height direction substantially parallel to the rotational shaft (O), characterized in that the blade has a skirt area close to the main plate (2) that is located more radially outward of the main plate (2) when coming closer to the main plate (2) at the blade leading edge (4a), and another skirt area close to the side plate (3) that is located more radially outward of the side plate (3) when coming closer to the side plate (3) at the blade leading edge (4a), andthe blade outer circumferential surface (4b) of the blade leading edge (4a) on the side of the main plate (2) curves outward of the main plate (2).
- The turbofan of claim 1, wherein, the blade (4) is connected at its end edge close to the side plate (3) to the side plate (3) in a region close to the blade trailing edge (4e), and is located at the side plate opening away from the side plate (3), in a region close to the blade leading edge (4a), and the blade trailing edge (4e) of the blade (4) has a wavy form having at least two inflection points located on a hypothetical cylinder connecting outer circumferential edges of the main plate (2) and the side plate (3) and has a main plate side curved portion projecting to a rotational direction in a region closer to the main plate (2) and a side plate side curved portion projecting in an opposite rotational direction in a region closer to the side plate (3).
- The turbofan of claim 1, wherein, in a region located at the side plate opening, an end edge of the blade (4) close to the side plate (3) curves so as to be located more radially outward as the end edge comes closer to the blade leading edge (4a) in a plan view, and expands so as to be positioned farther away from the end edge as its curved region comes closer to the blade leading edge (4a) in a side view.
- The turbofan of any one of claims 1 to 3, wherein a line connecting a portion where the blade trailing edge (4e) is joined to the main plate (2) and a portion where the blade trailing edge (4e) is joined to the side plate (3) is parallel to the rotational shaft (O).
- The turbofan of any one of claims 1 to 4, wherein the blade (4) has a taper-shaped, hollow structure having a hollow formed therein where the distance between the blade outer circumferential surface (4b) and the blade inner circumferential surface (4c) is gradually smaller toward the side plate (3) from the main plate (2).
- The turbofan of any one of claims 1 to 5, wherein a center line between the blade outer circumferential surface (4b) and the blade inner circumferential surface (4c) is parallel to the rotational shaft (O) in a region where the blade (4) is joined to the side plate (3).
- The turbofan of claim 2 or 4, wherein, in a side view of an end of the blade trailing edge (4e), an inclined line connecting a maximum projection (4ec2) in the rotational direction in the main plate side curved portion and a maximum projection (4ec3) in the opposite direction in the side plate curved portion is inclined at 10 to 30 degrees to a vertical line connecting a connecting portion with the main plate (2) and a connecting portion with the side plate (3).
- The turbofan of claim 2 or 4, wherein, a circumferential curvature angle (γ), which is an angle in a plan view, made by a line connecting a center of the rotational shaft (O) and an intersection of a horizontal camber line showing a center line between the blade outer circumferential surface (4b) and the blade inner circumferential surface (4c) and an outer circumferential edge of the main plate (2) in a plan view of the connecting portion with the main plate (2), and a line connecting the center of the rotational shaft (O) and the intersection of the horizontal camber line showing the center line between the blade outer circumferential surface (4b) and the blade inner circumferential surface (4c) and a circumferential edge of the side plate (3) in a plan view of the connecting portion with the side plate (3) is 5 to 15 degrees.
- The turbofan of claim 2 or 4, wherein an angular difference (Δβ2) between a main plate side outlet angle, in a plan view of the main plate side curved portion, formed between a tangent to a horizontal camber line showing a center line between the blade outer circumferential surface (4b) and the blade inner circumferential surface (4c) at an end of the blade trailing edge (4e) and a tangent at the end of the blade trailing edge (4e) to a circle passing through the end of the blade trailing edge (4e) having its center at the center of the rotational shaft (O), and a side plate side outlet angle, in a plan view of the side plate side curved portion, between a tangent to the horizontal camber line showing the center line between the blade outer circumferential surface (4b) and the blade inner circumferential surface (4c) at the end of the blade trailing edge (4e) and a tangent at the end of the blade trailing edge (4e) to the circle passing through the end of the blade trailing edge (4e) having its center at the center of the rotational shaft (O), is 20 to 35 degrees.
- The turbofan of claim 3, wherein, in a side view, a curvature angle (ε) which is an angle formed between a tangent at an end of the blade leading edge (4a) to the vertical camber line showing the center line between the blade outer circumferential surface (4b) and the blade inner circumferential surface (4c) and the rotational shaft (O) is 25 to 45 degrees.
- The turbofan of any one of claims 1 to 10, wherein, at an end of the blade leading edge (4a) in a plan view, a blade side plate side inlet angle that is an inlet angle at a position closer to the side plate (3), a blade middle inlet angle that is an inlet angle in the middle of the side plate (3) and the main plate (2) in a height direction, and a blade main plate side inlet angle that is an inlet angle at a position closer to the main plate (2) have a relationship of "the blade middle inlet angle > the blade main plate side inlet angle > the blade side plate side inlet angle".
- The turbofan of claim 11, wherein at the end of the blade leading edge (4a) in a plan view, an angular difference (Δβ1) between a blade middle inner circumferential inlet angle that is an inlet angle at an inner circumferential side end in the middle of the side plate (3) and the main plate (2) in a height direction and a blade side plate side inlet angle that is an inlet angle at an end closer to the side plate (3) is 10 to 20 degrees.
- The turbofan of claim 3, wherein a concave groove (5) is formed on the blade inner circumferential surface in the curved region of the blade (4) so as to extend to an end close to the side plate (3), a folding line (B) is defined at a boundary of the curved region and the blade inner circumferential surface except the curved region, and the concave groove (5) is substantially parallel to the folding line (B);
wherein, optionally, the concave groove (5) has a rectangular section and is gradually shallowing toward an end close to the side plate (3). - An air conditioning apparatus, wherein the turbofan of any one of claims 1 to 13 is mounted, and a ventilating pressure loss unit (12) is provided at an air inlet opening of the turbofan.
- An air conditioning apparatus, wherein the turbofan of any one of claims 1 to 13 is mounted, and a ventilating pressure loss unit (12) is provided at an air outlet opening of the turbofan.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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JP2008109046 | 2008-04-18 | ||
PCT/JP2009/054060 WO2009128299A1 (en) | 2008-04-18 | 2009-03-04 | Turbofan and air conditioner |
Publications (3)
Publication Number | Publication Date |
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EP2264320A1 EP2264320A1 (en) | 2010-12-22 |
EP2264320A4 EP2264320A4 (en) | 2015-04-15 |
EP2264320B1 true EP2264320B1 (en) | 2018-08-08 |
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EP09731652.5A Active EP2264320B1 (en) | 2008-04-18 | 2009-03-04 | Turbofan and air conditioner |
Country Status (6)
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EP (1) | EP2264320B1 (en) |
JP (2) | JP5283691B2 (en) |
CN (1) | CN101960150B (en) |
AU (1) | AU2009237152B2 (en) |
ES (1) | ES2686246T3 (en) |
WO (1) | WO2009128299A1 (en) |
Families Citing this family (42)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN100559031C (en) * | 2005-10-06 | 2009-11-11 | 三菱电机株式会社 | Turbofan and air conditioner |
JP5444108B2 (en) * | 2010-04-23 | 2014-03-19 | 東芝キヤリア株式会社 | Centrifugal fan and air conditioner |
JP5882804B2 (en) * | 2012-03-23 | 2016-03-09 | 三菱重工業株式会社 | Impeller and fluid machinery |
AU2013263811B2 (en) * | 2012-12-03 | 2018-03-15 | Angelo Lambrinos Notaras | Motorised Portable Blower Apparatus |
CN103174672B (en) * | 2013-04-02 | 2016-01-13 | 宁波朗迪叶轮机械有限公司 | BI oblique flow wind pushing impeller |
CN103174673B (en) * | 2013-04-02 | 2016-01-13 | 宁波朗迪叶轮机械有限公司 | Plastics blast device on air-conditioning |
CN103174674A (en) * | 2013-04-02 | 2013-06-26 | 宁波朗迪叶轮机械有限公司 | Oblique flow centrifugal impeller for air conditioner |
CN103195752B (en) * | 2013-04-03 | 2015-11-18 | 宁波朗迪叶轮机械有限公司 | A kind of impeller on air-conditioning |
CN103195753B (en) * | 2013-04-03 | 2015-12-02 | 宁波朗迪叶轮机械有限公司 | Backswept impeller |
CN103195751B (en) * | 2013-04-03 | 2015-11-04 | 宁波朗迪叶轮机械有限公司 | BI centrifugation blade |
CN103185030B (en) * | 2013-04-03 | 2015-12-02 | 宁波朗迪叶轮机械有限公司 | Inclined-flow centrifugal impeller on air-conditioning |
KR101677030B1 (en) | 2013-05-10 | 2016-11-17 | 엘지전자 주식회사 | Centrifugal fan |
EP2829733B1 (en) | 2013-05-10 | 2021-01-27 | Lg Electronics Inc. | Centrifugal fan |
EP3009686B1 (en) | 2013-06-13 | 2017-11-15 | Mitsubishi Heavy Industries, Ltd. | Impeller and fluid machine |
CN104895835B (en) * | 2014-03-05 | 2017-11-28 | 海尔集团公司 | A kind of centrifugal fan, the manufacture method of centrifugal fan and the air-conditioning with the centrifugal fan |
KR102227374B1 (en) * | 2014-05-28 | 2021-03-11 | 엘지전자 주식회사 | Centrifugal fan |
TWI550237B (en) * | 2014-06-06 | 2016-09-21 | 張永富 | Impeller structure for a kitchen ventilator |
JP2016050486A (en) * | 2014-08-29 | 2016-04-11 | 株式会社日立製作所 | Fluid machinery and impeller of fluid machinery |
JP2016142431A (en) * | 2015-01-30 | 2016-08-08 | ジョンソンコントロールズ ヒタチ エア コンディショニング テクノロジー(ホンコン)リミテッド | Air conditioner |
CN105987015A (en) * | 2015-02-26 | 2016-10-05 | 廖泊康 | 360-degree rotary type air blower |
KR101906341B1 (en) * | 2015-04-09 | 2018-10-12 | 코웨이 주식회사 | Air cleaner |
JP6621194B2 (en) * | 2015-06-03 | 2019-12-18 | 三星電子株式会社Samsung Electronics Co.,Ltd. | Turbofan and blower using the turbofan |
JP6053882B2 (en) * | 2015-07-28 | 2016-12-27 | 三菱重工業株式会社 | Impeller and fluid machinery |
JP6642913B2 (en) * | 2015-10-02 | 2020-02-12 | 三菱重工サーマルシステムズ株式会社 | Turbo fan and air conditioner using it |
CN105275875B (en) * | 2015-10-15 | 2017-12-26 | 珠海格力电器股份有限公司 | Centrifugation blade and centrifugal blower |
ES2792034T3 (en) | 2015-12-28 | 2020-11-06 | Daikin Ind Ltd | Procedure and apparatus for manufacturing a centrifugal fan impeller |
JP6056952B1 (en) * | 2015-12-28 | 2017-01-11 | ダイキン工業株式会社 | Centrifugal fan impeller and manufacturing method thereof |
JP6200531B2 (en) * | 2016-02-04 | 2017-09-20 | 三菱重工業株式会社 | Impeller and fluid machinery |
CN105864099B (en) * | 2016-05-24 | 2018-06-26 | 江苏大学 | A kind of design method of middle higher specific speed centrifugal pump impeller port of export edge folding blades structure |
WO2018020790A1 (en) * | 2016-07-27 | 2018-02-01 | 株式会社デンソー | Centrifugal blower |
WO2018020854A1 (en) * | 2016-07-27 | 2018-02-01 | 株式会社デンソー | Centrifugal blower |
CN106286388B (en) * | 2016-08-31 | 2019-05-24 | 泛仕达机电股份有限公司 | A kind of backward centrifugal blower |
JP6971662B2 (en) * | 2017-06-30 | 2021-11-24 | 株式会社川本製作所 | Impeller |
JP2019019759A (en) * | 2017-07-18 | 2019-02-07 | 日本電産株式会社 | Centrifugal fan impeller and centrifugal fan with centrifugal fan impeller |
CN110892201B (en) * | 2017-07-26 | 2021-05-11 | 三菱电机株式会社 | Air conditioner |
JP7467025B2 (en) * | 2018-03-26 | 2024-04-15 | 東芝キヤリア株式会社 | Blower and indoor unit of air conditioner |
JP6625291B1 (en) * | 2018-12-26 | 2019-12-25 | 三菱電機株式会社 | Impeller, blower and air conditioner |
CN109899318B (en) * | 2019-02-22 | 2021-03-30 | 宁波德业日用电器科技有限公司 | Vortex fan of new health air purifier |
CN110725808B (en) * | 2019-10-31 | 2021-03-02 | 中国科学院工程热物理研究所 | Centrifugal impeller blade, configuration method and centrifugal compressor |
CN111963478B (en) * | 2020-07-28 | 2021-10-01 | 宁波方太厨具有限公司 | Blade for centrifugal fan, centrifugal fan and range hood |
KR20220033352A (en) * | 2020-09-09 | 2022-03-16 | 삼성전자주식회사 | Fan, air conditioner having fan, and menufacturing method of fan |
JP2023156170A (en) * | 2022-04-12 | 2023-10-24 | 株式会社デンソー | centrifugal fan |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS53144508U (en) * | 1977-04-20 | 1978-11-14 | ||
JPS53144508A (en) * | 1977-05-20 | 1978-12-15 | Neos Kk | Process for preparing perfluoroolefin oligomer |
DE3137554A1 (en) * | 1981-09-22 | 1983-03-31 | Wilhelm Gebhardt Gmbh, 7112 Waldenburg | "RADIAL FAN" |
JP2701604B2 (en) | 1991-08-02 | 1998-01-21 | ダイキン工業株式会社 | Air conditioner |
JPH08165998A (en) * | 1994-12-14 | 1996-06-25 | Matsushita Refrig Co Ltd | Centrifugal blower |
JPH1030590A (en) | 1996-07-16 | 1998-02-03 | Matsushita Refrig Co Ltd | Centrifugal blower |
JPH1122695A (en) * | 1997-06-30 | 1999-01-26 | Ishikawajima Harima Heavy Ind Co Ltd | Impeller blade structure of centrifugal compressor |
JP2001234888A (en) * | 2000-02-25 | 2001-08-31 | Mitsubishi Heavy Ind Ltd | Blower |
JP3757802B2 (en) * | 2001-02-09 | 2006-03-22 | 三菱電機株式会社 | Turbofan, and blower and air conditioner using turbofan |
JP3861008B2 (en) * | 2002-01-10 | 2006-12-20 | 三菱重工業株式会社 | Turbofan and air conditioner equipped with the same |
JP4014887B2 (en) * | 2002-02-08 | 2007-11-28 | シャープ株式会社 | Centrifugal fan and cooking device equipped with the centrifugal fan |
CN1712736A (en) * | 2004-06-15 | 2005-12-28 | 松下电器产业株式会社 | Wind turbine device and manufacture thereof |
CN100559031C (en) * | 2005-10-06 | 2009-11-11 | 三菱电机株式会社 | Turbofan and air conditioner |
KR20070101642A (en) * | 2006-04-11 | 2007-10-17 | 삼성전자주식회사 | Turbo fan |
JP2008002379A (en) * | 2006-06-23 | 2008-01-10 | Daikin Ind Ltd | Centrifugal fan |
KR20080045568A (en) * | 2006-11-20 | 2008-05-23 | 삼성전자주식회사 | Turbofan and air conditioner having the same |
-
2009
- 2009-03-04 CN CN200980106559.XA patent/CN101960150B/en active Active
- 2009-03-04 EP EP09731652.5A patent/EP2264320B1/en active Active
- 2009-03-04 WO PCT/JP2009/054060 patent/WO2009128299A1/en active Application Filing
- 2009-03-04 ES ES09731652.5T patent/ES2686246T3/en active Active
- 2009-03-04 JP JP2010508146A patent/JP5283691B2/en active Active
- 2009-03-04 AU AU2009237152A patent/AU2009237152B2/en active Active
-
2013
- 2013-03-18 JP JP2013055150A patent/JP5669877B2/en active Active
Non-Patent Citations (1)
Title |
---|
None * |
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JP2013117233A (en) | 2013-06-13 |
WO2009128299A1 (en) | 2009-10-22 |
ES2686246T3 (en) | 2018-10-17 |
JP5669877B2 (en) | 2015-02-18 |
CN101960150B (en) | 2014-04-02 |
JP5283691B2 (en) | 2013-09-04 |
AU2009237152B2 (en) | 2012-07-05 |
EP2264320A1 (en) | 2010-12-22 |
JPWO2009128299A1 (en) | 2011-08-04 |
AU2009237152A1 (en) | 2009-10-22 |
CN101960150A (en) | 2011-01-26 |
EP2264320A4 (en) | 2015-04-15 |
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