EP2905474B1 - Propellerlüfter - Google Patents

Propellerlüfter Download PDF

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Publication number
EP2905474B1
EP2905474B1 EP12886000.4A EP12886000A EP2905474B1 EP 2905474 B1 EP2905474 B1 EP 2905474B1 EP 12886000 A EP12886000 A EP 12886000A EP 2905474 B1 EP2905474 B1 EP 2905474B1
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EP
European Patent Office
Prior art keywords
propeller fan
imaginary line
blade
blades
pair
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.)
Active
Application number
EP12886000.4A
Other languages
English (en)
French (fr)
Other versions
EP2905474A4 (de
EP2905474A1 (de
Inventor
Atsushi Kono
Takahide Tadokoro
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Electric Corp
Original Assignee
Mitsubishi Electric Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Mitsubishi Electric Corp filed Critical Mitsubishi Electric Corp
Publication of EP2905474A1 publication Critical patent/EP2905474A1/de
Publication of EP2905474A4 publication Critical patent/EP2905474A4/de
Application granted granted Critical
Publication of EP2905474B1 publication Critical patent/EP2905474B1/de
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Classifications

    • 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
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • 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
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/329—Details of the hub
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/002—Axial flow fans

Definitions

  • the present invention relates to a propeller fan, an air blower, and an outdoor unit.
  • a propeller fan includes a cylindrical boss connected to a driving source, and a plurality of blades extending in a radiate manner from an outer peripheral surface of the boss.
  • JP 2012-052443 A see mainly Fig. 1
  • JP 2012-052443 A there is disclosed such a configuration that, in each blade, a position at which a camber ratio is maximum is set to a position closer to a blade root portion than an outer peripheral edge of the blade, and the camber ratio is gradually decreased toward the blade root portion from the position at which the camber ratio is maximum.
  • JPS6357896A discloses a method wherein a recessed part is formed in the front of the shaft part on the suction side of a fan, and an air flow passage, through which the interior and the exterior of the recessedpart is intercommunicated, is formed in the peripheral surface of the shaft part of the fan.
  • JPH0431697A discloses a vane structure to reduce noise and to improve blowing efficiency of an axial flow blower by constructing the vane structure of the blower with first blades arranged far from the center and second blades arranged close to the center.
  • US4150919A discloses a fan construction of the type having a hoop configured hub provided with fan blades.
  • the hub has apertures adjacent the blade roots.
  • a viscous drive carries the hub. Rotation of the fan causes a pressure differential between the two ends of each hub aperture thus forcing an airflow radially outward to assist in cooling the viscous drive.
  • the Coriolis force acting in a direction reverse to a rotating direction of the propeller fan balances with a pressure gradient between adjacent blade surfaces, and thus an air current between the blades flows along the blades.
  • the above-mentioned pressure gradient influences up to the outer peripheral surface of the boss, whereas relative velocity of the air current is low in a boundary layer on the outer peripheral surface of the boss, with the result that the Coriolis force is reduced. Accordingly, the above-mentioned balance is lost in the vicinity of the outer peripheral surface of the boss, and due to the influence of the above-mentioned pressure gradient, a secondary flow toward an adjacent blade is generated. The secondary flow collides with the blade, and thus a vortex occurs, which causes noise.
  • the camber ratio is gradually decreased toward the blade root portion from the position at which the camber ratio is maximum, thereby being capable of suppressing a vortex, which may occur at a connecting portion between the blade and the boss.
  • an amount of work of the blade is reduced in the vicinity of the connecting portion between the blade and the boss.
  • the present invention has been made in view of the above, and has an object to provide a propeller fan capable of suppressing a vortex, which may occur at a connecting portion between a blade and a boss, thereby reducing a noise level of the fan without depending on setting of a camber ratio of the blade in the vicinity of a blade root portion.
  • a propeller fan according to claim 1 is provided.
  • an air blower including: the above-mentioned propeller fan according to the invention; a driving source for applying a driving force to the propeller fan; and a casing in which the propeller fan and the driving source are housed.
  • an outdoor unit including: a heat exchanger; the above-mentioned propeller fan according to the invention; a driving source for applying a driving force to the propeller fan; and a casing in which the propeller fan, the driving source, and the heat exchanger are housed.
  • the propeller fan according to the present invention it is possible to suppress the vortex, which may occur at the connecting portion between the blade and the boss, thereby reducing the noise level of the fan without depending on the setting of the camber ratio of the blade in the vicinity of the blade root portion.
  • FIG. 1 is a perspective view illustrating a propeller fan according to a first embodiment of the present invention as viewed from a downstream side.
  • FIGS. 2 , 3 , and 4 are a side view illustrating the propeller fan, a view illustrating an air current flowing over an outer peripheral surface of a boss, and a view illustrating an air current passing through a slit, respectively.
  • a propeller fan 1 includes a boss section 3 and a plurality of blades 5.
  • the boss section 3 includes a tubular wall 3a having a cylindrical shape.
  • An output shaft of a driving source such as a motor is connected to a center portion 3b of the boss section 3, and the propeller fan 1 is rotated by a driving force of the driving source.
  • reference symbol RD of FIG. 1 represents a rotating direction of the propeller fan 1
  • reference symbol RA of FIG. 2 represents a rotation axis of the propeller fan 1.
  • Reference symbol US conceptually represents an upstream air current
  • reference symbol DS conceptually represents a downstream air current.
  • a downstream end of the tubular wall 3a of the boss section 3 is closed by a lid plate portion 3c.
  • an upstream end of the tubular wall 3a of the boss section 3 is open.
  • the plurality of blades 5 extend in a radiate manner from an outer peripheral surface 3d of the tubular wall 3a of the boss section 3. Further, the plurality of blades 5 have mutually the same shape, and are provided at equal intervals.
  • the blades 5 each include an outer peripheral edge 5a, a blade root portion 5b, a leading edge 5c, a trailing edge 5d, a positive pressure surface 5e, and a negative pressure surface 5f.
  • the outer peripheral edge 5a is an edge portion of each blade 5 on a radially outer side thereof, and is also an edge portion extending in a circumferential direction.
  • the blade root portion 5b is a portion of each blade 5 connected to the outer peripheral surface 3d of the boss section 3.
  • the leading edge 5c is an edge portion connecting a leading end of the outer peripheral edge 5a and a leading end of the blade root portion 5b, and is also an edge portion on a forward side in the rotating direction of the propeller fan 1.
  • the trailing edge 5d is an edge portion connecting a trailing end of the outer peripheral edge 5a and a trailing end of the blade root portion 5b, and is also an edge portion on a backward side in the rotating direction of the propeller fan 1. In the illustrated configuration, both the leading edge 5c and the trailing edge 5d are curved so as to extend onward in the rotating direction toward the radially outer side.
  • the positive pressure surface 5e and the negative pressure surface 5f are each a blade surface defined by the outer peripheral edge 5a, the blade root portion 5b, the leading edge 5c, and the trailing edge 5d.
  • the positive pressure surface 5e and the negative pressure surface 5f are positioned so as to have a mutually front-and-back relationship .
  • the positive pressure surface 5e is a blade surface on a downstream side of an air current generated through rotation of the propeller fan 1
  • the negative pressure surface 5f is a blade surface on an upstream side of the air current.
  • the positive pressure surface 5e is a concave surface concaved toward the downstream side
  • the negative pressure surface 5f is a convex surface convexed toward the upstream side.
  • Secondary flow control slits 7 are each formed between a pair of adjacent blades 5 on the outer peripheral surface 3d of the boss section 3. As illustrated best in FIG. 4 , each of the plurality of secondary flow control slits 7 in the entire outer peripheral surface 3d of the boss section 3 passes through the tubular wall 3a of the boss section 3 to communicate between the inside of the boss section 3 and the outside of the boss section 3.
  • each of the plurality of secondary flow control slits 7 extends obliquely to the rotation axis RA of the propeller fan, and extends obliquely in the same direction as a forming direction of the blade root portion 5b of each of the plurality of blades 5.
  • each of the secondary flow control slits 7 extends straight in side view, and is inclined so that a forward portion thereof in the rotating direction of the propeller fan is positioned on the upstream side of the air current.
  • an air current flowing into the propeller fan from the upstream side flows from the vicinity of a leading edge 55c of a positive pressure surface 55e of the blade 55 toward a negative pressure surface 55f of an adjacent blade 55, and then flows to the downstream side while forming a vortex.
  • the Coriolis force acting in a direction reverse to the rotating direction balances with a pressure gradient from the positive pressure surface 55e of the blade 55 to the negative pressure surface 55f of the adjacent blade 55, and thus the air current between the blades 55 is formed into a flow along the blades 55.
  • the above-mentioned pressure gradient influences up to the outer peripheral surface of the boss section 53, whereas relative velocity of the air current is low in a boundary layer on the outer peripheral surface of the boss section 53, with the result that the Coriolis force is reduced. Accordingly, due to the influence of the above-mentioned pressure gradient, a secondary flow toward the negative pressure surface of the adjacent blade is generated. The secondary flow collides with the negative pressure surface, and thus a vortex occurs.
  • an upstream end surface of the boss section 3 is open, and the inside of the boss section 3 is communicated to the upstream side of the propeller fan 1.
  • the secondary flow control slit 7 connecting the inside and the outside of the boss section 3 is formed across a region between the blades. Accordingly, in a case where pressure in the region between the blades is higher than pressure in the inside of the boss section 3, as indicated by the solid arrow F1 of FIGS. 3 and 4 , the secondary flow is sucked into the inside of the boss section 3 through the secondary flow control slit 7 formed in the outer peripheral surface 3d of the boss section 3.
  • the secondary flow is separated from the boundary layer on the outer peripheral surface 3d of the boss section 3, and hence the air current flowing toward the negative pressure surface 5f can be suppressed. Accordingly, it is possible to suppress turbulence of the air current, which may be caused by occurrence of a vortex.
  • the secondary flow control slit 7 is inclined in the same direction as a direction of inclination of the blades 5. Hence, the secondary flow control slit 7 can exert a reduced action on the air current parallel to the blades 5.
  • the secondary flow control slit 7 is orthogonal to the secondary flow, thereby being capable of increasing the above-mentioned effect of suppressing occurrence of a vortex.
  • the secondary flow control slit suppresses a vortex, which may occur at a connecting portion between the blade and the boss, thereby being capable of reducing the noise level of the fan. Further, this configuration does not depend on setting of a camber ratio of the blade in the vicinity of the blade root portion, thereby being capable of suppressing occurrence of a vortex while causing the blade to effectively work on a region up to the vicinity of the blade root portion.
  • FIG. 5 is a view illustrating a position of a slit formed in the outer peripheral surface of the boss according to a second embodiment of the present invention.
  • FIG. 5 illustrates a partial developed state of the outer peripheral surface 3d of the boss section 3.
  • FIG. 5 illustrates the blade root portions 5b of the pair of blades 5 and a secondary flow control slit 107 positioned between the blade root portions 5b.
  • the secondary flow control slit 107 is formed in a range between the imaginary line VL1 and the imaginary line VL2. Note that, the other features of the secondary flow control slit 107 may be the same as those of the above-mentioned secondary flow control slit 7 according to the first embodiment.
  • the secondary flow control slit is limitedly formed in a range in which the pressure gradient between the blades is large and the secondary flow is easily generated, and hence it is possible to suppress occurrence of a vortex while reducing an influence on a primary flow.
  • FIG. 6 is a view illustrating a position of a slit formed in the outer peripheral surface of the boss according to a third embodiment of the present invention, and is also a view similar to FIG. 5 .
  • an imaginary line VL3 is assumed.
  • the imaginary line VL3 extends along an intermediate position between the pair of adjacent blades (blade root portions 5b) in a circumferential direction. More specifically, the imaginary line VL3 is a line obtained by aligning, from a pair of leading edges to a pair of trailing edges, circumferential middle points between a pair of camber lines (blade thickness center lines) CL of the pair of adjacent blades.
  • a secondary flow control slit 207 extends in a range between the imaginary line VL1 and the imaginary line VL2, and is arranged in a forward region in the rotating direction RD of the propeller fan with respect to the imaginary line VL3. Note that, the other features of the secondary flow control slit 207 may be the same as those of the above-mentioned secondary flow control slit 7 according to the first embodiment.
  • the same advantage as that of the above-mentioned second embodiment can be obtained.
  • the secondary flow control slit 207 is formed at a position closer to the negative pressure surface 5f where the secondary flow becomes strongest (that is, a position closer to the negative pressure surface 5f than the positive pressure surface 5e), and hence an effect of suppressing the secondary flow can be significantly obtained.
  • FIG. 7 is a view illustrating a position of a slit formed in the outer peripheral surface of the boss according to a fourth embodiment of the present invention, and is also a view similar to FIG. 5 .
  • imaginary lines VL4 and VL5 are assumed.
  • the imaginary line VL4 is a line positioned at equal distances from the pair of imaginary lines VL1 and VL2.
  • the imaginary line VL4 is a line extending along an intermediate position between the pair of imaginary lines VL1 and VL2 in a direction of the rotation axis of the propeller fan.
  • P represents an intersection point between the imaginary line VL4 and the camber line (blade thickness center line) CL of the forward blade 5 of the pair of corresponding blades 5 in the rotating direction RD of the propeller fan
  • a line segment joining the leading edge 5c of the corresponding backward blade 5 and the intersection point P on the corresponding forward blade 5 is assumed as the imaginary line VL5.
  • a secondary flow control slit 307 extends in the range between the imaginary line VL1 and the imaginary line VL2, and is arranged in the forward region in the rotating direction RD of the propeller fan with respect to the imaginary line VL3 and in a backward region in the rotating direction RD of the propeller fan with respect to the imaginary line VL5.
  • the secondary flow control slit 307 is arranged in a region surrounded by the imaginary line VL2, the imaginary line VL3, the imaginary line VL5, and the forward blade 5 of the pair of corresponding blades 5 in the rotating direction RD of the propeller fan.
  • the other features of the secondary flow control slit 207 may be the same as those of the above-mentioned secondary flow control slit 7 according to the first embodiment.
  • the same advantage as that of the above-mentioned third embodiment can be obtained.
  • the secondary flow is considerably easily generated in a region ranging from the vicinity of the leading edge of the backward blade connected to the boss section to the vicinity of a midpoint between the leading edge and the trailing edge of the adj acent forward blade or the trailing edge of the adjacent forward blade.
  • the fourth embodiment has such an advantage that an action exerted by the secondary flow control slit can be obtained more intensively in the region where the secondary flow is considerably easily generated.
  • FIG. 8 is a view illustrating a position of a slit formed in the outer peripheral surface of the boss according to a fifth embodiment of the present invention, and is also a view similar to FIG. 5 .
  • a secondary flow control slit 407 according to the fifth embodiment extends in parallel to a camber of the blade 5.
  • the secondary flow control slit 407 illustrated in FIG. 8 is a limited example of the fifth embodiment.
  • the secondary flow control slit 407 is further formed so as to be curved in parallel to the camber of the blade 5.
  • the secondary flow control slit according to the fifth embodiment corresponds to the secondary flow control slit according to any one of the above-mentioned first to fourth embodiments, which extends in parallel to the camber of the blade, and is not always limited to the state illustrated in FIG. 8 .
  • the secondary flow control slit is parallel also to the primary flow of the air current generated between the blades, and hence it is possible to reduce the influence on the primary flow.
  • FIG. 9 is a view illustrating a position of a slit formed in the outer peripheral surface of the boss according to a sixth embodiment of the present invention, and is also a view similar to FIG. 5 .
  • a secondary flow control slit 507 according to the sixth embodiment extends so as to have a width of one tenth or less of a circumferential inter-blade distance L between the pair of corresponding blades 5 (dimension in a direction orthogonal to an extending direction of the slit).
  • the other configurations of the secondary flow control slit 507 are the same as those of the secondary flow control slit according to any one of the above-mentioned first to fifth embodiments.
  • FIG. 11 is a perspective view illustrating an outdoor unit (air blower) according to a seventh embodiment as viewed from an air outlet side thereof
  • FIG. 12 is a view illustrating a configuration of the outdoor unit as viewed from a top surface side thereof.
  • FIG. 13 illustrates a state in which a fan grille is removed
  • FIG. 14 is a view illustrating an internal configuration in a state in which a front panel and the like are further removed.
  • an outdoor-unit main body (casing) 51 is formed as a casing including a pair of right and left side surfaces 51a, 51c, a front surface 51b, a back surface 51d, a top surface 51e, and a bottom surface 51f.
  • the side surface 51a and the back surface 51d each have an opening portion through which the air is sucked from an outside of the outdoor-unit main body (see the arrows A of FIG. 12 ).
  • an air outlet 53 is formed as an opening portion through which the air is blown out to the outside (see the arrows A of FIG. 12 ).
  • the air outlet 53 is covered with a fan grille 54. This configuration prevents contact between an object, etc. and the propeller fan 1, to thereby assure safety.
  • the propeller fan 1 is mounted in the outdoor-unit main body 51.
  • the propeller fan 1 is the propeller fan according to any one of the above-mentioned first to sixth embodiments.
  • the propeller fan 1 is connected to a fan motor (driving source) 61 on the back surface 51d side through intermediation of a rotation shaft 62, and is rotated and driven by the fan motor 61.
  • An inside of the outdoor-unit main body 51 is partitioned by a partition plate (wall) 51g into an air-blowing chamber 56 in which the propeller fan 1 is housed and mounted, and a machine chamber 57 in which a compressor 64 and the like are mounted.
  • a heat exchanger 68 extending in substantially an L-shape in plan view is provided.
  • a bellmouth 63 is arranged on a radially outer side of the propeller fan 1 arranged in the air-blowing chamber 56.
  • the bellmouth 63 is positioned on an outer side of the outer peripheral edge of each of the blades 5, and exhibits an annular shape along the rotating direction of the propeller fan 1.
  • the partition plate 51g is positioned on one side of the bellmouth 63 (on a right side in the drawing sheet of FIG. 12 ), and apart of the heat exchanger 68 is positioned on another side (opposite side) thereof (on a left side in the drawing sheet of FIG. 12 ).
  • a front end of the bellmouth 63 is connected to the front panel 52 of the outdoor unit so as to surround an outer periphery of the air outlet 53.
  • the bellmouth 63 may be formed integrally with the front panel 52, or may be prepared as a separate component to be connected to the front panel 52. Due to the bellmouth 63, a flow passage between an air inlet side and an air outlet side of the bellmouth 63 is formed as an air passage in the vicinity of the air outlet 53. That is, the air passage in the vicinity of the air outlet 3 is partitioned by the bellmouth 63 from another space in the air-blowing chamber 56.
  • the heat exchanger 68 provided on the air inlet side of the propeller fan 1 includes a plurality of fins aligned side by side so that respective plate-like surfaces are parallel to each other, and heat-transfer pipes passing through the respective fins in analigning direction of the fins.
  • a refrigerant which circulates through a refrigerant circuit, flows in the heat-transfer pipes.
  • the heat-transfer pipes extend in an L-shape along the side surface 51a and the back surface 51d of the outdoor-unit main body 51, and as illustrated in FIG. 14 , the heat-transfer pipes in a plurality of tiers are configured so as to pass through the fins in a zigzag manner.
  • the heat exchanger 68 is connected to the compressor 64 through piping 65 or the like.
  • the heat exchanger 68 is connected to an indoor-side heat exchanger, an expansion valve, and the like (not shown) so as to form a refrigerant circuit of an air conditioner.
  • a board box 66 is arranged in the machine chamber 7. Devices mounted in the outdoor unit are controlled by a control board 67 provided in the board box 66.
  • the outdoor unit of the air conditioner is exemplified as an outdoor unit including anairblower.
  • the present invention is not limited thereto, but can be implemented as, for example, an outdoor unit of a hot-water supply device or the like.
  • the present invention can be widely employed as an apparatus for blowing the air, and can be applied to an apparatus, equipment, and the like other than the outdoor unit.
  • the present invention is widely applicable to, for example, outdoor units of an air blower, an air conditioner, a hot-water supply device, and the like, and to a heat exchanger of a refrigerating cycle.

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  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

  1. Propellerlüfter (1), umfassend:
    eine Nabe (3), die eine röhrenförmige Wand (3a) umfasst; und
    mehrere Schaufeln (5), die an einer Außenumfangsfläche (3d) der röhrenförmigen Wand (3a) der Nabe (3) vorgesehen sind und sich radial von dieser erstrecken,
    wobei ein Schlitz (7, 107, 207, 307, 407, 507) zwischen jedem Paar der benachbarten Schaufeln auf der Außenumfangsfläche (3d) ausgebildet ist,
    wobei jeder der mehreren Schlitze durch die röhrenförmige Wand (3a) verläuft, um eine kommunizierende Verbindung zwischen einem Inneren der Nabe (3) und einem Äußeren der Nabe (3) herzustellen,
    wobei ein stromabwärtiges Ende der röhrenförmigen Wand (3a) geschlossen ist, während ein stromaufwärtiges Ende der röhrenförmigen Wand (3a) offen ist, und
    wobei, in Seitenansicht, jeder der mehreren Schlitze schräg zu einer Drehachse (RA) des Propellerlüfters verläuft und in die gleiche Richtung wie eine Formrichtung eines Schaufelfußabschnitts (5b) von jeder der mehreren Schaufeln (5) verläuft.
  2. Propellerlüfter (1) nach Anspruch 1, wobei unter der Annahme, dass VL1 eine gedachte Linie darstellt, die mehrere Eintrittskanten an Stellen der Schaufelfußabschnitte der Schaufeln (5) verbindet, und VL2 eine gedachte Linie darstellt, die mehrere Austrittskanten verbindet, jeder der Schlitze in einem Bereich zwischen der gedachten Linie VL1 und der gedachten Linie V12 ausgebildet ist.
  3. Propellerlüfter (1) nach Anspruch 2, wobei unter der Annahme, dass VL3 eine gedachte Linie VL darstellt, die entlang einer Zwischenstelle zwischen dem Paar benachbarter Schaufeln (5) verläuft, jeder der Schlitze in einer vorderen Region in einer Drehrichtung des Propellerlüfters (1) bezüglich der gedachten Linie VL3 angeordnet ist, wobei die gedachte Linie VL3 eine Linie ist, die durch Ausrichten von einem Paar Eintrittskanten zu einem Paar Austrittskanten von Umfangsmittelpunkten zwischen einem Paar Wölbungslinien CL des Paars benachbarter Schaufeln erhalten wird.
  4. Propellerlüfter (1) nach Anspruch 3, wobei unter der Annahme, dass eine in gleichen Abständen von dem Paar gedachter Linien VL1 und VL2 positionierte Linie als eine gedachte Linie VL4 dargestellt wird und dass, wenn P einen Schnittpunkt zwischen der gedachten Linie VL4 und einer Wölbungslinie der vorderen Schaufel eines Paars der entsprechenden Schaufeln in der Drehrichtung des Propellerlüfters (1) darstellt, ein eine Eintrittskante einer entsprechenden hinteren Schaufel und den Schnittpunkt P auf der entsprechenden vorderen Schaufel verbindendes Liniensegment als eine gedachte Linie VL5 dargestellt wird, jeder der Schlitze in einer rückwärtigen Region in der Drehrichtung des Propellerlüfters (1) bezüglich der gedachten Linie VL5 angeordnet ist.
  5. Propellerlüfter (1) nach einem der Ansprüche 1 bis 4, wobei jeder der Schlitze parallel zu einer Wölbung der Schaufel (5) verläuft.
  6. Propellerlüfter (1) nach einem der Ansprüche 1 bis 5, wobei jeder der Schlitze eine Breite von einem Zehntel oder weniger eines Umfangsabstands (L) zwischen dem Paar der entsprechenden Schaufeln (5) aufweist.
  7. Luftgebläse, umfassend:
    den Propellerlüfter (1) nach einem der Ansprüche 1 bis 6;
    eine Antriebsquelle (61) zum Anlegen einer Antriebskraft an den Propellerlüfter (1); und
    ein Gehäuse (51), in dem der Propellerlüfter (1) und die Antriebsquelle (61) untergebracht sind.
  8. Außeneinheit, umfassend:
    einen Wärmetauscher (68);
    den Propellerlüfter (1) nach einem der Ansprüche 1 bis 6;
    eine Antriebsquelle (61) zum Anlegen einer Antriebskraft an den Propellerlüfter (1); und
    ein Gehäuse (51), in dem der Propellerlüfter (1), die Antriebsquelle (61) und der Wärmetauscher (68) untergebracht sind.
EP12886000.4A 2012-10-03 2012-10-03 Propellerlüfter Active EP2905474B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2012/075656 WO2014054132A1 (ja) 2012-10-03 2012-10-03 プロペラファン

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USD910834S1 (en) * 2018-12-05 2021-02-16 Asia Vital Components Co., Ltd. Impeller for a fan
CN111692128B (zh) * 2020-05-21 2021-12-10 西安交通大学 一种跨音压气机组合机匣处理结构

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CN104685218A (zh) 2015-06-03
WO2014054132A1 (ja) 2014-04-10
JP5984162B2 (ja) 2016-09-06
CN104685218B (zh) 2018-03-16
EP2905474A4 (de) 2016-07-06
EP2905474A1 (de) 2015-08-12
US20150204345A1 (en) 2015-07-23
JPWO2014054132A1 (ja) 2016-08-25

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