EP3315786A1 - Turbolüfter und klimaanlage damit - Google Patents

Turbolüfter und klimaanlage damit Download PDF

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Publication number
EP3315786A1
EP3315786A1 EP16851050.1A EP16851050A EP3315786A1 EP 3315786 A1 EP3315786 A1 EP 3315786A1 EP 16851050 A EP16851050 A EP 16851050A EP 3315786 A1 EP3315786 A1 EP 3315786A1
Authority
EP
European Patent Office
Prior art keywords
blade
air flow
hub
shroud
joining part
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.)
Withdrawn
Application number
EP16851050.1A
Other languages
English (en)
French (fr)
Other versions
EP3315786A4 (de
Inventor
Tsuyoshi Eguchi
Soichiro Matsumoto
Hirofumi Ishizuka
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 Heavy Industries Thermal Systems Ltd
Original Assignee
Mitsubishi Heavy Industries Thermal Systems Ltd
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 Heavy Industries Thermal Systems Ltd filed Critical Mitsubishi Heavy Industries Thermal Systems Ltd
Publication of EP3315786A1 publication Critical patent/EP3315786A1/de
Publication of EP3315786A4 publication Critical patent/EP3315786A4/de
Withdrawn legal-status Critical Current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
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • 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
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade

Definitions

  • the present invention relates to a turbofan which blows out the air suctioned in an axial direction from a shroud side by changing a direction into a radial direction, and an air conditioner in which the same is used.
  • a turbofan is configured of a hub which is driven in a rotating manner by a motor or the like, a shroud which is positioned facing the hub, and a plurality of blades which are positioned between the hub and the shroud.
  • a leading edge which is an end portion on an inner peripheral side is positioned further on a rotation direction side than a trailing edge which is an end portion on an outer peripheral side in many cases, or the blade of the turbofan is molded in a shape of a blade in many cases between the hub and the shroud, but a sectional shape thereof is generally a uniform two-dimensional shape in the axial direction due to a restriction or the like on molding (for example, refer to PTL 1 or the like).
  • the restriction of a manufacturing method has been eliminated, and a blade having a three-dimensional shape in the axial direction or a blade having a hollow shape has been suggested in many cases (for example, refer to PTL 2 to PTL 4).
  • a technology for targeting low noise or high efficiency and focusing on performance for example, as illustrated in PTL 5 to PTL 7, a technology in which a structure in which the vicinity of a leading edge on a hub side of a blade is curved in the rotation direction or in a counter-rotation direction is achieved, and a horseshoe-shaped swirl suppressing section is formed for suppressing a horseshoe-shape swirl generated at a joining part between the hub and the blade, a technology in which a dead water region reducing space is supposed to be formed between a blade and a shroud, and a part of the blade is formed to be curved in the counter-rotation direction, and is connected to an arc surface of the shroud via the bent portion, or a technology in which a hub side of a trailing edge of a blade is curved in both of the rotation direction and the counter-rotation direction, and an air flow can be accelerated in a trailing edge of the blade, are suggested.
  • the air flow suctioned from an outer edge side of a suction opening is not curved and cut by an inertial force, and is likely to be a flow deviated to a hub side on the inside, the blade does not efficiently function at a location near the suction opening, efficiency deterioration is caused, a high-speed jet flow is generated by deviation of the air flow on a blow-out side, a counterflow is generated in the vicinity of the suction opening, and noise is likely to increase.
  • the turbofan in an air conditioner, the air is suctioned from a quadrangular passage via a grill or a filter, the turbofan is operated in a non-axis symmetric pressure field surrounded by a heat exchanger of which the blow-out side has a quadrangular shape, and thus, it is difficult to realize a uniform flow across the entire spanwise direction (axial direction) of the fan, and as described above, various ideas targeting low noise or high efficiency are suggested.
  • an object of the invention is to provide a turbofan which can improve a fan efficiency and can reduce a fan input which is a driving force of a fan, by suppressing separation of an air flow on a suction surface on an outer peripheral side (trailing edge side) of the blade and by suppressing a decrease in speed of the air flow on a pressure surface side of the blade, and an air conditioner in which the same is used.
  • the turbofan and the air conditioner in which the same is used of the present invention employs the following means.
  • a turbofan including: a hub which is connected to a motor drive shaft, and is driven in a rotating manner; an annular shroud which is positioned facing the hub and forms an air suction opening; and a plurality of blades having both end portions joined between the hub and the shroud so that leading edges on the inner peripheral side are positioned on a rotation direction side of trailing edges on the outer peripheral side, in which the plurality of blades are configured such that the trailing edges are made into recesses in the counter-air flow direction relative to joining parts to the hub and the shroud.
  • the plurality of blades are configured such that the trailing edges (also referred to as trailing edge lines) are made into recesses in the counter-air flow direction relative to joining parts to the hub and the shroud, compared to a case where the trailing edge lines of the blades are made into straight lines or into projections in the air flow direction, it is possible to improve separation of the air flow on a suction surface side of the blade, and to suppress disturbance of the air flow, and it is possible to improve a fan efficiency by reducing a high static pressure region generated on a pressure surface side of the blade and by suppressing a decrease in speed of the air flow (a loss of the driving force), and to reduce the driving force (fan input) of the fan.
  • a center part in a spanwise direction of the blade may be made into recesses in the counter-air flow direction within a range of 25% to 75% in the spanwise direction.
  • the center part of the trailing edge line of the blade is made into recesses in the counter-air flow direction within a range of 25% to 75% in the spanwise direction of the blade, it is possible to join the blade to the hub and the shroud without influencing the function and performance of the joining part of the blade to the hub and the shroud. Therefore, it is possible to achieve low noise and high efficiency without disturbing the air flow in a hub side joining part and a shroud side joining part of the blade.
  • a recess amount (expressed as -) in the counter-air flow direction of the trailing edge of the blade may be within a range of -0.0142D to -0.0153D, with respect to a fan outer diameter D.
  • the recess amount (expressed as -) in the counter-air flow direction of the trailing edge line of the blade is within a range of - 0.0142D to -0.0153D, with respect to a fan outer diameter D, it is possible to reduce the fan input which is the driving force of the turbofan to be in a preferable range. Therefore, it is possible to achieve high efficiency and low noise of the turbofan.
  • leading edges of the blades may be made into recesses in an air flow direction or may be made into projections in the counter-air flow direction relative to joining parts to the hub and the shroud.
  • leading edges also referred to as leading edge lines
  • leading edge lines are made into recesses in the air flow direction or are made into projections in the counter-air flow direction relative to joining parts to the hub and the shroud
  • the length in the air flow direction of the blade is shortened by making the leading edge lines of the blade into recesses in the air flow direction, and it is possible to reduce a friction loss between the air flow and the blade surface, and to reduce the fan input.
  • the leading edge lines are made into extreme recesses, the blade length in the air flow direction with respect to the distance between adjacent blades becomes extremely short, and blade performance deteriorates.
  • the friction loss between the air flow and the blade surface generally increases.
  • the length in the air flow direction of the blade is substantially long, by stably guiding the flow that flows in from the blade upstream side to the downstream side, it is possible to make it difficult to separate the flow by suppressing a peak value of the static pressure on the blade surface, to reduce the fan input, and to reduce fan noise. Therefore, in this case, it is also possible to sufficiently reduce the fan input, and to achieve high efficiency and low noise of the turbofan.
  • a recess amount (expressed as +) in the air flow direction of the leading edge of the blade may be within a range of 0.0091D to 0.0153D, with respect to the fan outer diameter D, and a projection amount (expressed as -) in the counter-air flow direction may be -0.0438D with respect to the fan outer diameter D.
  • the recess amount (expressed as +) in the air flow direction of the leading edge line is within a range of 0.0091D to 0.0153D, with respect to the fan outer diameter D, and the projection amount (expressed as -) in the counter-air flow direction is -0.0438D with respect to the fan outer diameter D, it is possible to reduce the fan input which is the driving force of the turbofan to be in a preferable range, and according to this, it is possible to achieve high efficiency and low noise of the turbofan.
  • a center part in the spanwise direction of the blade may be made into recesses in the air flow direction or into projections in the counter-air flow direction within a range of 25% to 75% in the spanwise direction.
  • the center part of the leading edge line of the blade is made into recesses in the air flow direction or into projections in the counter-air flow direction within a range of 25% to 75% in the spanwise direction of the blade, it is possible to join the blade with the hub and the shroud without influencing the function and performance of the joining part of the blade to the hub and the shroud. Therefore, it is possible to achieve low noise and high efficiency without disturbing the air flow at the hub side joining part and the shroud side joining part of the blade.
  • the joining part of the blade to the hub may be made into a smooth curved surface in the counter-rotation direction
  • the joining part of the blade to the shroud may be made into a smooth curved surface in a rotation direction.
  • the joining part of the blade to the hub is configured to be a smooth curved surface in the counter-rotation direction
  • the joining part of the blade to the shroud is configured to be a smooth curved surface in the rotation direction
  • by making the joining part of the blade to the hub into a smooth curved surface in the counter-rotation direction it is possible to set the joining part to be horizontally asymmetric, and to suppress stagnation of the air flow at the joining part.
  • by making the joining part of the blade to the shroud into a smooth curved surface in the rotation direction it is possible to suppress separation of the flow on the suction surface side by a blade force and to make the air flow smooth. Therefore, it is possible to improve blade performance, and to achieve high efficiency by further reducing the fan input, and it is possible to suppress disturbance of the air flow, and to achieve low noise.
  • an angle (expressed as +) of the curved surface in the counter-rotation direction of the joining part of the blade to the hub may be within a range of 0.0563 ⁇ to 0.0972 ⁇ with respect to one pitch angle ⁇ of the blade
  • an angle (expressed as -) of the curved surface in the rotation direction of the joining part to the shroud may be within a range of -0.0154 ⁇ to -0.0972 ⁇ with respect to one pitch angle ⁇ of the blade.
  • the angle (expressed as +) of the curved surface in the counter-rotation direction of the joining part of the blade to the hub is within a range of 0.0563 ⁇ to 0.0972 ⁇ with respect to one pitch angle ⁇ of the blade
  • the angle (expressed as -) of the curved surface in the rotation direction of the joining part to the shroud is within a range of -0.0154 ⁇ to -0.0972 ⁇ with respect to one pitch angle ⁇ of the blade
  • the joining part of the blade to the hub may be made into a smooth curved surface in the rotation direction, and the joining part of the blade to the shroud may be made into a smooth curved surface in the counter-rotation direction.
  • the joining part of the blade to the hub is made into a smooth curved surface in the rotation direction
  • the joining part of the blade to the shroud is made into a smooth curved surface in the counter-rotation direction
  • by making the joining part of the blade to the shroud into a smooth curved surface in the rotation direction it is possible to make the air flow on the suction surface side in the vicinity of the shroud smooth, and to suppress separation. Therefore, it is possible to improve blade performance, and to achieve high efficiency by further reducing the fan input, and it is possible to suppress disturbance of the air flow, and to achieve low noise.
  • an angle (expressed as -) of the curved surface in the rotation direction of the joining part of the blade to the hub may be -0.0768 ⁇ with respect to one pitch angle ⁇ of the blade
  • an angle (expressed as +) of the curved surface in the counter-rotation direction of the joining part to the shroud may be 0.0031 ⁇ with respect to one pitch angle ⁇ of the blade.
  • the angle (expressed as -) of the curved surface in the rotation direction of the joining part of the blade to the hub is -0.0768 ⁇ with respect to one pitch angle ⁇ of the blade
  • the angle (expressed as +) of the curved surface in the counter-rotation direction of the joining part to the shroud is 0.0031 ⁇ with respect to one pitch angle ⁇ of the blade
  • the joining part of the blade to the hub may be made into a smooth curved surface in the rotation direction
  • the joining part of the blade to the shroud may be made into a smooth curved surface in the rotation direction
  • the joining part of the blade to the hub is made into a smooth curved surface in the rotation direction
  • the joining part of the blade to the shroud is made into a smooth curved surface in the rotation direction
  • by making the joining part of the blade to the shroud into a smooth curved surface in the rotation direction it is possible to suppress separation of the flow on the suction surface side by the blade force, and to make the air flow smooth. Therefore, it is possible to improve blade performance, and to achieve high efficiency by further reducing the fan input, and it is possible to suppress disturbance of the air flow, and to achieve low noise.
  • the angle (expressed as -) of the curved surface in the rotation direction of the joining part of the blade to the hub may be -0.0154 ⁇ with respect to one pitch angle ⁇ of the blade
  • the angle (expressed as -) of the curved surface in the rotation direction of the joining part to the shroud may be -0.0461 ⁇ with respect to one pitch angle ⁇ of the blade.
  • the angle (expressed as -) of the curved surface in the rotation direction of the joining part of the blade to the hub is -0.0154 ⁇ with respect to one pitch angle ⁇ of the blade
  • the angle (expressed as -) of the curved surface in the rotation direction of the joining part to the shroud is -0.0461 ⁇ with respect to one pitch angle ⁇ of the blade
  • an air conditioner including: a fan which suctions and blows out indoor air; and a heat exchanger which is positioned on any of a suction side and a blow-out side of the blower, and cools or heats the indoor air, in which the fan is configured of the turbofan according to any of the above-described turbofans.
  • the fan suctions the indoor air, cools or heats the indoor air by the heat exchanger, and blows out the temperature-adjusted air into an indoor space is configured to be any of the above-described turbofans, it is possible to reduce the fan input which is the driving force of the turbofan, and to achieve high efficiency and low noise of the turbofan. Therefore, it is possible to achieve higher performance and lower noise of the air conditioner.
  • turbofan of the invention it is possible to improve separation of the air flow on the suction surface side of the blade, and to suppress disturbance of the air flow, and it is possible to reduce the high static pressure region generated on the pressure surface side of the blade, and to improve the fan efficiency by suppressing the decrease in speed (a loss of the driving force) of the air flow, and to reduce the driving force (fan input) of the fan, and thus, it is possible to achieve higher efficiency and lower noise of the turbofan.
  • the air conditioner of the invention it is possible to reduce the fan input which is the driving force of the turbofan, and to achieve high efficiency and low noise of the turbofan, and thus, it is possible to achieve higher performance and lower noise of the air conditioner.
  • FIG. 1 an exploded perspective view of an air conditioner according to one embodiment of the present invention is illustrated.
  • An air conditioner 1 according to the embodiment is a ceiling bury type air conditioner 1, but the present invention is not limited to the ceiling bury type air conditioner 1, and it is needless to say that the present invention may be employed in other types of air conditioner 1.
  • the ceiling bury type air conditioner 1 includes a substantially rectangular unit main body 2 which is hanged and installed by a bolt or the like in the ceiling; a four-sided ceiling panel 3 including an indoor air suction opening 4 and a temperature-adjusted air blow-out opening 5 which are provided on a lower surface of the unit main body 2; a bell mouth 6 which is positioned in the unit main body 2 to face the indoor air suction opening 4 of the ceiling panel 3; a turbofan (fan) 7 which is installed to be fixed to the ceiling of the unit main body 2 to face the bell mouth 6; and a quadrangular heat exchanger 8 which is installed in the unit main body 2 to surround the turbofan (fan) 7.
  • the turbofan 7 is a fan having a casingless structure including: a motor 9 which is installed to be fixed to the ceiling of the unit main body 2; a hub (main plate) 10 which is joined to a rotating shaft 9A of the motor 9, and is driven in a rotating manner by the motor 9; an annular shroud (side plate) 11 which is positioned to face the hub (main plate) 10; and a plurality of blades 12 having both end portions joined between the hub (main plate) 10 and the shroud (side plate) 11.
  • a leading edge (there is also a case of being referred to as a leading edge line) 13 on an inner peripheral side is positioned on the rotation direction N side of a trailing edge (there is also a case of being referred to as a trailing edge line) 14 on an outer peripheral side.
  • the shape of the blade 12 is investigated as follows, and according to this, an air flow on a suction surface 15 side of the blade 12 is illustrated as a fine streamline that has a small sudden change in interval (no separation) similar to a limit streamline (a line which visualizes a flow of a blade surface in a shape of a line) illustrated in Fig. 2B , and a static pressure on a pressure surface 16 side of the blade 12 is set to have no high static pressure region, or to have extremely small high static pressure region similar to a static pressure contour view illustrated in Fig. 2C , and is set such that a decrease in speed (loss) of the air flow is suppressed and a fan input which is a driving force of the turbofan 7 is reduced.
  • the performance of the turbofan 7 is supposed to be evaluated regarding the fan input which is the driving force of the turbofan 7 as a parameter, is analyzed by a finite volume method in a state where the turbofan 7 is mounted on the air conditioner 1, and sets the shape of the blade 12 based on the analysis.
  • the fluid analysis as illustrated in Fig. 14A , by using four design parameters, such as (1) displacement (moving amount) of the leading edge 13 of the blade 12, (2) displacement (moving amount) of a trailing edge 14 of the blade 12, (3) curve (rotation angle) of a hub side joining part 17 of the blade 12, and (4) curve (rotation angle) of a shroud side joining part 18 of the blade 12, the evaluation is performed with respect to the parameter study of 41 cases.
  • a first shape (No. 31) in the parameter study as a base the most appropriate shape (No. 59) is acquired.
  • Figs. 2A and 3A to 3E illustrate shapes of a fan (No. 59) having the most appropriate shape, fans which are the first (No. 31), the second (No. 32), and the third (No. 06) among 41 cases evaluated in the parameter study, a fan (No. 0) having an original shape which is an evaluation reference, and a fan (No. 14) which is in the lowest place (41-st) in evaluation.
  • a fan No. 0
  • a fan No. 14
  • Specific shapes of the fans illustrated in Figs. 2A and 3A to 3E will be described later, but as illustrated in Fig.
  • the fan having an original shape has a configuration in which the shape of a section of the blade 12 is a uniform two-dimensional shape in an axial direction, both of the leading edge line 13 and the trailing edge line 14 of the blade 12 are parallel straight lines, and the hub side joining part 17 and the shroud side joining part 18 which join both ends of the blade 12 with the hub 10 and the shroud 11 are joined substantially perpendicularly with the hub 10 and the shroud 11.
  • the leading edge line 13 of the blade 12 is made into a recess 13A in the air flow direction
  • the trailing edge line 14 is made into a projection 14B in the air flow direction
  • the hub side joining part 17 is made into a curved surface 17A curved in the counter-rotation direction
  • the shroud side joining part 18 is made into a curved surface 18A curved in the counter-rotation direction.
  • FIGs. 4A to 4E and 5A to 5E views in which limit streamlines and static pressure contours of each of the fans that correspond to the fan shape illustrated in Figs. 3A to 3E , are compared to each other, are illustrated.
  • all of the blades are curved in the counter-rotation direction (counterclockwise direction) or in the rotation direction (clockwise direction) with respect to a center O of the rotating shaft 9A such that the angle made by the blade 12 and the air flow does not change.
  • the displacement (moving amount) of the leading edge 13 and the trailing edge 14 of the blade 12 as illustrated in Fig. 11 , by setting the outer diameter direction of the blade 12 to be a + direction, on a camber line and an extending line thereof in the blade 12, the displacement is performed into recesses or projections.
  • the displacement of the leading edge 13 and the trailing edge 14 of the blade 12 is moved only by the same amount along the camber line within a substantial range of 25% to 75% of the blade height in the spanwise direction (rotating shaft direction) on both of the leading edge 13 side and the trailing edge 14 side, and the leading edge 13 and the trailing edge 14 are made into recesses or projections.
  • the hub 10 and the shroud 11 are configured to be connected to each other by a smooth curved line.
  • a blade force BF of the turbofan 7 is exploded.
  • the blade force BF of the turbofan 7 corresponds to a pressure gradient that acts between the plurality of blades (blades 12), and is a force given by the blade to the air flow which is a fluid, and as illustrated in Fig. 13 , by inclining the blades (blades 12), the blade force BF acts in the direction perpendicular to the blade surface.
  • the blade force BF achieves an action for suppressing separation on the suction surface side by pressing the air flow onto the wall surface (in Fig. 13 , a wall surface of the shroud 11).
  • Fig. 2A is a perspective view of the turbofan 7 including the blade 12 which has the most appropriate shape of the case No. 59.
  • the blade 12 is configured such that the leading edge line 13 is made into the recess 13A (refer to Fig. 6B ) in the air flow direction, and the trailing edge line 14 is made into the recess 14A (refer to Fig. 7B ) in the counter-air flow direction.
  • the joining part (hub side joining part) 17 to the hub 10 of the blade 12 is made into the curved surface 17A (refer to Fig. 8B ) which is curved in the counter-rotation direction (counterclockwise direction), and the joining part (shroud side joining part) 18 to the shroud 11 of the blade 12 is made into the curved surface 18B (refer to Fig. 9C ) which is curved in the rotation direction (clockwise direction).
  • the hub side joining part 17 and the shroud side joining part 18 as illustrated in Fig. 10 , all of the blades are curved around the center O of the rotating shaft such that the angle made by the blade 12 and the air flow does not change.
  • leading edge line 13 and the trailing edge line 14 as illustrated in Figs. 11 and 12 , as the center part in the spanwise direction (rotating shaft direction) of the blade 12 moves by the same amount on the camber line and the extending line thereof of the blade 12 within a range of 25 to 75% of a dimension in the spanwise direction, the leading edge line 13 is made into the recess 13A in the air flow direction and the trailing edge line 14 is made into the recess 14A in the counter-air flow direction.
  • the above-described design parameters (1) to (4) include (1) the displacement (moving amount) of the leading edge (pull-LE) 13 of the blade 12 is made into the recess 13A having approximately 0.0153D in the air flow direction (expressed as +), and (2) the displacement (moving amount) of the trailing edge (pull-TE) 14 of the blade 12 is made into the recess 14A having approximately -0.0153D in the counter-air flow direction (expressed as -).
  • Fig. 3A a perspective view of the turbofan 7 having a blade shape of the case No. 31 (first) is illustrated.
  • the blade 12 is the same as the blade 12 having the most appropriate shape, the leading edge line 13 is configured to be made into the recess 13A (refer to Fig. 6B ) in the air flow direction, and the trailing edge line 14 is configured to be made into the recess 14A (refer to Fig. 7B ) in the counter-air flow direction.
  • the joining part 17 (hub side joining part) to the hub 10 of the blade 12 is configured to be made into the curved surface 17A (refer to Fig. 8B ) curved in the counter-rotation direction (counterclockwise direction), and the joining part (shroud side joining part) 18 to the shroud 11 of the blade 12 is configured to be made into the curved surface 18B (refer to Fig. 9C ) curved in the rotation direction (clockwise direction).
  • the hub side joining part 17 and the shroud side joining part 18 as illustrated in Fig. 10 , all of the blades are curved around the center O of the rotating shaft such that the angle made by the blade 12 and the air flow does not change.
  • leading edge line 13 and the trailing edge line 14 as illustrated in Figs. 11 and 12 , as the center part in the spanwise direction (rotating shaft direction) of the blade 12 moves by the same amount on the camber line and the extending line thereof of the blade 12 within a range of 25 to 75% of a dimension in the spanwise direction, the leading edge line 13 is made into the recess 13A in the air flow direction and the trailing edge line 14 is made into the recess 14A in the counter-air flow direction.
  • the above-described design parameters (1) to (4) include (1) the displacement (moving amount) of the leading edge (pull-LE) 13 of the blade 12 is made into the recess 13A having approximately 0.0153D with respect to the air flow direction (expressed as +), and (2) the displacement (moving amount) of the trailing edge (pull-TE) 14 of the blade 12 is made into the recess 14A having approximately -0.0153D with respect to the counter-air flow direction (expressed as -).
  • Fig. 3B a perspective view of the turbofan 7 having a blade shape of the case No. 32 (second) is illustrated.
  • the blade 12 is the same as the blade 12 having the most appropriate shape, the leading edge line 13 is configured to be made into the recess 13A (refer to Fig. 6B ) in the air flow direction, and the trailing edge line 14 is configured to be made into the recess 14A (refer to Fig. 7B ) in the counter-air flow direction.
  • the joining part 17 (hub side joining part) to the hub 10 of the blade 12 is configured to be made into the curved surface 17B (refer to Fig. 8C ) curved in the rotation direction (clockwise direction), and the joining part (shroud side joining part) 18 to the shroud 11 of the blade 12 is configured to be made into the curved surface 18A (refer to Fig. 9B ) curved in the counter-rotation direction (counterclockwise direction).
  • the hub side joining part 17 and the shroud side joining part 18 as illustrated in Fig. 10 , all of the blades are curved around the center O of the rotating shaft such that the angle made by the blade 12 and the air flow does not change.
  • leading edge line 13 and the trailing edge line 14 as illustrated in Figs. 11 and 12 , as the center part in the spanwise direction (rotating shaft direction) of the blade 12 moves by the same amount on the camber line and the extending line thereof of the blade 12 within a range of 25 to 75% of a dimension in the spanwise direction, the leading edge line 13 is made into the recess 13A in the air flow direction and the trailing edge line 14 is made into the recess 14A in the counter-air flow direction.
  • the above-described design parameters (1) to (4) include (1) the displacement (moving amount) of the leading edge (pull-LE) 13 of the blade 12 is made into the recess 13A having approximately 0.0091D with respect to the air flow direction (expressed as +), and (2) the displacement (moving amount) of the trailing edge (pull-TE) 14 of the blade 12 is made into the recess 14A having approximately -0.0142D in the counter-air flow direction (expressed as -).
  • Fig. 3C a perspective view of the turbofan 7 having a blade shape of the case No. 06 (third) is illustrated.
  • the leading edge line 13 is configured to be made into the projection 13B (refer to Fig. 6C ) in the counter-air flow direction
  • the trailing edge line 14 is configured to be made into the recess 14A (refer to Fig. 7B ) in the counter-air flow direction.
  • the joining part 17 (hub side joining part) to the hub 10 of the blade 12 is configured to be made into the curved surface 17B (refer to Fig. 8C ) curved in the rotation direction (clockwise direction), and the joining part (shroud side joining part) 18 to the shroud 11 of the blade 12 is configured to be made into the curved surface 18B (refer to Fig. 9C ) curved in the counter-rotation direction (counterclockwise direction).
  • the hub side joining part 17 and the shroud side joining part 18 as illustrated in Fig. 10 , all of the blades are curved around the center O of the rotating shaft such that the angle made by the blade 12 and the air flow does not change.
  • leading edge line 13 and the trailing edge line 14 as illustrated in Figs. 11 and 12 , as the center part in the spanwise direction (rotating shaft direction) of the blade 12 moves by the same amount on the camber line and the extending line thereof of the blade 12 within a range of 25 to 75% of a dimension in the spanwise direction, the leading edge line 13 is configured to be made into the projection 13B in the counter-air flow direction and the trailing edge line 14 is configured to be made into the recess 14A in the counter-air flow direction.
  • the above-described design parameters (1) to (4) include (1) the displacement (moving amount) of the leading edge (pull-LE) 13 of the blade 12 is made into the projection 13B having approximately -0.0438D in the counter-air flow direction (expressed as -), and (2) the displacement (moving amount) of the trailing edge (pull-TE) 14 of the blade 12 is made into the recess 14A having approximately -0.0153D in the counter-air flow direction (expressed as -).
  • any of four design parameters (1) to (4) is set to be 0.
  • the blade shape of the case No. 14 (41-st) which is in the lowest place in evaluation (1) the displacement (moving amount) of the leading edge (pull-LE) 13 of the blade 12 is made into the recess 13A having approximately 0.0153D in the air flow direction (expressed as +), (2) the displacement (moving amount) of the trailing edge (pull-TE) 14 is made into the projection 14B having approximately 0.0438D in the air flow direction (expressed as +), (3) the curve (rotation angle) of the hub side joining part 17 of the blade 12 is made into the curved surface 17A having 0.05630 in the counter-rotation direction (expressed as +), and (4) the curve (rotation angle) of the shroud side joining part 18 is made into the curved surface 18A having 0.0358 ⁇ in the counter-rotation direction (expressed as +).
  • the indoor air suctioned from the indoor air suction opening 4 of the ceiling panel 3 by the rotation of the turbofan 7 is suctioned in the axial direction from an opening portion on the shroud 11 side of the turbofan 7 via the bell mouth 6.
  • the air flow suctioned to the turbofan 7 is blown out after changing the direction into the radial direction by the plurality of blades 12, is cooled or heated in the process of passing through the heat exchanger 8 positioned to surround the turbofan 7, and accordingly, the air flow is blown out to the indoor space from the four temperature-adjusted air blow-out openings 5 provided on four sides of the ceiling panel 3 as the temperature-adjusted air, and is provided for conditioning the air in the indoor space.
  • the turbofan 7 in order to change the direction of the air flow suctioned in the axial direction into the radial direction (centrifugal direction), in particular, the air flow suctioned from the vicinity of the outer edge (shroud 11 side) of the suction opening is not bent and cut by an inertial force, and is likely to be a flow deviated to the hub 10 side on the inside of the fan, the blade 12 does not efficiently function on a side near the shroud 11, efficiency deterioration is caused, a high-speed jet flow is generated by deviation of the air flow on a blow-out side, a counterflow is generated on the suction side, and aerodynamic noise is likely to increase.
  • the turbofan in the air conditioner 1 the air is suctioned from a quadrangular air duct, the turbofan is operated in a non-axis symmetric pressure field surrounded by the quadrangular heat exchanger 8 in many cases, and it is difficult to realize a uniform flow across the entire spanwise direction of the fan.
  • the fluid analysis by the finite volume method is parametrically performed, and the shape of the blade 12 is set based on the values of the design parameters.
  • Fig. 14B the definition of a objective function D' is illustrated.
  • values of the design parameters in the analysis result by the finite volume method are summarized.
  • Fig. 16 with respect to the above-described objective function D', the values of the above-described six cases are compared to each other and are illustrated in the bar graph, and in Figs. 17 to 20 , graphs illustrating a correlation between the objective function D' and the design parameter (1), the objective function D' and the design parameter (2), the objective function D' and the design parameter (3), and the objective function D' and the design parameter (4), are illustrated.
  • the air flow on the suction surface 15 side of the blade 12 can be a fine streamline of which the rapid change of the interval is small (no separation) similar to limit streamline (a case where the flow of the blade surface is visualized in a line shape) illustrated in Fig. 2B or Figs. 4A to 4C .
  • the static pressure (blade surface pressure) is distributed, but as the static pressure increases or as the high static pressure region increases, the speed of the air flow which is along the blade 12 is reduced, the fan efficiency deteriorates due to the loss.
  • the turbofan 7 of the embodiment regarding the high static pressure region, as illustrated in the static pressure contour views illustrated in Fig. 2C or Figs. 5A to 5C , compared to the cases illustrated in Figs. 5D and 5E , it is possible to reduce the pressure or to reduce the region.
  • a high static pressure region Y generated on the pressure surface 16 of the blade 12 is generated as a relatively large region Y as illustrated in Figs. 5D and 5E .
  • the high static pressure region Y is not generated or an extremely small region Y is generated, a decrease in speed of the air flow is not generated, and it is determined that the fan efficiency does not deteriorate by the loss caused by the increase in speed.
  • making the trailing edge line 14 into the recess 14A in the counter-air flow direction may be performed within a range of 25 to 75% of the center part in the spanwise direction, and does not influence the functions and performance of the joining parts 17 and 18 to the hub 10 and the shroud 11, and it is possible to join the blade 12 with the hub 10 and the shroud 11. Therefore, without disturbance of the air flow at the hub side joining part 17 and the shroud side joining part 18, it is possible to achieve low noise and high efficiency.
  • the recess amount (expressed as -) in the counter-air flow direction of the trailing edge line 14 of the blade 12 is within the range of - 0.0142D to -0.0153D when the outer diameter of the turbofan 7 is set to be D, as illustrated in Figs. 16 and 18 , it is possible to reduce the fan input which is the driving force of the turbofan 7 to be in a preferable range.
  • the center part of the leading edge line 13 of the blade 12 is made into the recess 13A in the air flow direction relative to the joining parts 17 and 18 to the hub 10 and the shroud 11 as illustrated in Fig. 2A or Figs. 3A and 3B , or is made into the projection 13B in the counter-air flow direction as illustrated in Fig. 3C , within the range of 25 to 75% in the spanwise direction (rotating shaft direction).
  • the length in the air flow direction of the blade 12 is substantially long, by stably guiding the flow that flows in from the blade upstream side to the downstream side, it is possible to make it difficult to separate the flow by suppressing a peak value of the static pressure on the surface of the blade 12, and to reduce the fan input, and it is possible to reduce the fan noise.
  • the joining part (hub side joining part) 17 to the hub 10 of the blade 12 is configured to be made into the smooth curved surface 17A in the counter-rotation direction
  • the joining part (shroud side joining part) 18 to the shroud 11 of the blade 12 is configured to be made into the smooth curved surface 18B in the rotation direction.
  • the angle (expressed as +) of the curved surface 17A in the counter-rotation direction of the joining part (hub side joining part) 17 to the hub 10 of the blade 12 is set to be within a range of 0.0563 ⁇ to 0.0972 ⁇ with respect to one pitch angle ⁇ of the blade 12, and the angle (expressed as -) of the curved surface 18B in the rotation direction of the joining part (shroud side joining part) 18 to the shroud 11 is set to be within a range of -0.0154 ⁇ to -0.0972 ⁇ with respect to the one pitch angle ⁇ of the blade.
  • the present invention is not limited to the invention according to the embodiment, and can be appropriately changed within a range that does not depart from the spirit of the invention.
  • the invention in the above-described embodiment, an example in which the invention is employed in the ceiling bury type air conditioner 1 in which the heat exchanger 8 is installed on the blow-out side of the turbofan 7 is described, but not being limited thereto, it is needless to say that it is also possible to employ the invention in the air conditioner 1 in the air conditioner or the like which suctions the temperature-adjusted air after exchanging heat through a heat exchanger having a shape of a flat surface and blows out the air to the indoor space from the upper and lower blow-out openings in the centrifugal direction.
  • the turbofan 7 itself may be employed in equipment other than the air conditioner.

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  • 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)
EP16851050.1A 2015-10-02 2016-09-06 Turbolüfter und klimaanlage damit Withdrawn EP3315786A4 (de)

Applications Claiming Priority (2)

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JP2015196839A JP6642913B2 (ja) 2015-10-02 2015-10-02 ターボファンおよびそれを用いた空気調和機
PCT/JP2016/076156 WO2017056874A1 (ja) 2015-10-02 2016-09-06 ターボファンおよびそれを用いた空気調和機

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DE1058200B (de) * 1952-02-27 1959-05-27 Bruno Eck Dr Ing Blechschaufelrad fuer Radialgeblaese und meridianbeschleunigte Axialgeblaese
JP2008144667A (ja) * 2006-12-11 2008-06-26 Daikin Ind Ltd 送風機の羽根車
JP2009127541A (ja) * 2007-11-26 2009-06-11 Daikin Ind Ltd 遠心ファン
JP4396775B2 (ja) * 2007-11-26 2010-01-13 ダイキン工業株式会社 遠心ファン
ES2686246T3 (es) * 2008-04-18 2018-10-17 Mitsubishi Electric Corporation Turboventilador y aparato acondicionador de aire
JP4994421B2 (ja) * 2009-05-08 2012-08-08 三菱電機株式会社 遠心ファン及び空気調和機
JP5444108B2 (ja) * 2010-04-23 2014-03-19 東芝キヤリア株式会社 遠心ファン及び空気調和機
JP6078945B2 (ja) * 2011-11-04 2017-02-15 ダイキン工業株式会社 遠心送風機
JP5590016B2 (ja) * 2011-12-14 2014-09-17 三菱電機株式会社 ターボファン、空気調和装置
WO2014061094A1 (ja) * 2012-10-16 2014-04-24 三菱電機株式会社 ターボファンおよび空気調和機

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CN107850081A (zh) 2018-03-27
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WO2017056874A1 (ja) 2017-04-06
EP3315786A4 (de) 2018-07-04
JP2017067056A (ja) 2017-04-06

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