US20150204345A1 - Propeller fan - Google Patents

Propeller fan Download PDF

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Publication number
US20150204345A1
US20150204345A1 US14/423,495 US201214423495A US2015204345A1 US 20150204345 A1 US20150204345 A1 US 20150204345A1 US 201214423495 A US201214423495 A US 201214423495A US 2015204345 A1 US2015204345 A1 US 2015204345A1
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US
United States
Prior art keywords
propeller fan
blades
imaginary line
blade
slit
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.)
Abandoned
Application number
US14/423,495
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English (en)
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
Assigned to MITSUBISHI ELECTRIC CORPORATION reassignment MITSUBISHI ELECTRIC CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KONO, ATSUSHI, TADOKORO, TAKAHIDE
Publication of US20150204345A1 publication Critical patent/US20150204345A1/en
Abandoned legal-status Critical Current

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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.
  • Patent Literature 1 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.
  • 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 including: a boss section including a tubular wall; and a plurality of blades extending in a radiate manner from an outer peripheral surface of the tubular wall of the boss section.
  • Secondary flow control slits are each formed between a pair of the adjacent blades on the outer peripheral surface.
  • Each of a plurality of the secondary flow control slits passes through the tubular wall to communicate between an inside of the boss section and an outside of the boss section. A downstream end of the tubular wall is closed, whereas an upstream end of the tubular wall is open.
  • each of the plurality of the secondary flow control slits extends obliquely to a rotation axis of the propeller fan, and extends obliquely in the same direction as a forming direction of a blade root portion of each of the plurality of blades.
  • an air blower including: the above-mentioned propeller fan according to the one embodiment of the present 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 one embodiment of the present 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 one embodiment of 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.
  • FIG. 2 is a side view illustrating the propeller fan according to the first embodiment.
  • FIG. 3 is a view illustrating an air current flowing over an outer peripheral surface of a boss of the propeller fan according to the first embodiment.
  • FIG. 4 is a view illustrating an air current passing through a slit in the outer peripheral surface of the boss of the propeller fan according to the first embodiment.
  • 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. 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.
  • 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.
  • FIG. 8 is a view illustrating a shape of a slit formed in the outer peripheral surface of the boss according to a fifth embodiment of the present invention.
  • FIG. 9 is a view illustrating a shape of a slit formed in the outer peripheral surface of the boss according to a sixth embodiment of the present invention.
  • FIG. 10 is a view illustrating an air current passing between blades of a propeller fan according to a comparative example.
  • FIG. 11 is a perspective view illustrating an outdoor unit according to a seventh embodiment of the present invention as viewed from an air outlet side thereof.
  • FIG. 12 is a view illustrating a configuration of the outdoor unit according to the seventh embodiment as viewed from a top surface side thereof.
  • FIG. 13 is a view illustrating a state in which a fan grille is removed according to the seventh embodiment.
  • FIG. 14 is a view illustrating an internal configuration in a state in which a front panel and the like are further removed according to the seventh embodiment.
  • 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 3 a having a cylindrical shape.
  • An output shaft of a driving source such as a motor is connected to a center portion 3 b 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 3 a of the boss section 3 is closed by a lid plate portion 3 c.
  • an upstream end of the tubular wall 3 a of the boss section 3 is open.
  • the plurality of blades 5 extend in a radiate manner from an outer peripheral surface 3 d of the tubular wall 3 a 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 5 a, a blade root portion 5 b, a leading edge 5 c, a trailing edge 5 d, a positive pressure surface 5 e, and a negative pressure surface 5 f.
  • the outer peripheral edge 5 a 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 5 b is a portion of each blade 5 connected to the outer peripheral surface 3 d of the boss section 3 .
  • the leading edge 5 c is an edge portion connecting a leading end of the outer peripheral edge 5 a and a leading end of the blade root portion 5 b, and is also an edge portion on a forward side in the rotating direction of the propeller fan 1 .
  • the trailing edge 5 d is an edge portion connecting a trailing end of the outer peripheral edge 5 a and a trailing end of the blade root portion 5 b, and is also an edge portion on a backward side in the rotating direction of the propeller fan 1 .
  • both the leading edge 5 c and the trailing edge 5 d are curved so as to extend onward in the rotating direction toward the radially outer side.
  • the positive pressure surface 5 e and the negative pressure surface 5 f are each a blade surface defined by the outer peripheral edge 5 a, the blade root portion 5 b, the leading edge 5 c, and the trailing edge 5 d.
  • the positive pressure surface 5 e and the negative pressure surface 5 f are positioned so as to have a mutually front-and-back relationship.
  • the positive pressure surface 5 e is a blade surface on a downstream side of an air current generated through rotation of the propeller fan 1
  • the negative pressure surface 5 f is a blade surface on an upstream side of the air current.
  • the positive pressure surface 5 e is a concave surface concaved toward the downstream side
  • the negative pressure surface 5 f 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 3 d 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 3 d of the boss section 3 passes through the tubular wall 3 a 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 5 b 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 55 c of a positive pressure surface 55 e of the blade 55 toward a negative pressure surface 55 f 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 55 e of the blade 55 to the negative pressure surface 55 f 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 F 1 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 3 d of the boss section 3 .
  • the secondary flow is separated from the boundary layer on the outer peripheral surface 3 d of the boss section 3 , and hence the air current flowing toward the negative pressure surface 5 f 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 3 d of the boss section 3 .
  • FIG. 5 illustrates the blade root portions 5 b of the pair of blades 5 and a secondary flow control slit 107 positioned between the blade root portions 5 b.
  • the secondary flow control slit 107 is formed in a range between the imaginary line VL 1 and the imaginary line VL 2 . 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 VL 3 is assumed.
  • the imaginary line VL 3 extends along an intermediate position between the pair of adjacent blades (blade root portions 5 b ) in a circumferential direction. More specifically, the imaginary line VL 3 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 VL 1 and the imaginary line VL 2 , and is arranged in a forward region in the rotating direction RD of the propeller fan with respect to the imaginary line VL 3 .
  • 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 5 f where the secondary flow becomes strongest (that is, a position closer to the negative pressure surface 5 f than the positive pressure surface 5 e ), 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 VL 4 and VL 5 are assumed.
  • the imaginary line VL 4 is a line positioned at equal distances from the pair of imaginary lines VL 1 and VL 2 .
  • the imaginary line VL 4 is a line extending along an intermediate position between the pair of imaginary lines VL 1 and VL 2 in a direction of the rotation axis of the propeller fan.
  • P represents an intersection point between the imaginary line VL 4 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 5 c of the corresponding backward blade 5 and the intersection point P on the corresponding forward blade 5 is assumed as the imaginary line VL 5 .
  • a secondary flow control slit 307 extends in the range between the imaginary line VL 1 and the imaginary line VL 2 , and is arranged in the forward region in the rotating direction RD of the propeller fan with respect to the imaginary line VL 3 and in a backward region in the rotating direction RD of the propeller fan with respect to the imaginary line VL 5 .
  • the secondary flow control slit 307 is arranged in a region surrounded by the imaginary line VL 2 , the imaginary line VL 3 , the imaginary line VL 5 , 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 adjacent 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 anyone 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 51 a, 51 c, a front surface 51 b, aback surface 51 d, a top surface 51 e, and a bottom surface 51 f.
  • the side surface 51 a and the back surface 51 d 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 51 d 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) 51 g 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 51 g is positioned on one side of the bellmouth 63 (on a right side in the drawing sheet of FIG. 12 ), and a part 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 an aligning 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 51 a and the back surface 51 d 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 an air blower.
  • 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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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US14/423,495 2012-10-03 2012-10-03 Propeller fan Abandoned US20150204345A1 (en)

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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US20150204345A1 true US20150204345A1 (en) 2015-07-23

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US14/423,495 Abandoned US20150204345A1 (en) 2012-10-03 2012-10-03 Propeller fan

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US (1) US20150204345A1 (ja)
EP (1) EP2905474B1 (ja)
JP (1) JP5984162B2 (ja)
CN (1) CN104685218B (ja)
WO (1) WO2014054132A1 (ja)

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USD910834S1 (en) * 2018-12-05 2021-02-16 Asia Vital Components Co., Ltd. Impeller for a fan

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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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EP2905474A1 (en) 2015-08-12
CN104685218B (zh) 2018-03-16
JPWO2014054132A1 (ja) 2016-08-25
WO2014054132A1 (ja) 2014-04-10
CN104685218A (zh) 2015-06-03
EP2905474A4 (en) 2016-07-06
EP2905474B1 (en) 2019-08-28

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