CN107850081B - Turbofan and the air-conditioning for having used the turbofan - Google Patents
Turbofan and the air-conditioning for having used the turbofan Download PDFInfo
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- CN107850081B CN107850081B CN201680042586.5A CN201680042586A CN107850081B CN 107850081 B CN107850081 B CN 107850081B CN 201680042586 A CN201680042586 A CN 201680042586A CN 107850081 B CN107850081 B CN 107850081B
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- Prior art keywords
- blade
- engaging portion
- rotation
- turbofan
- wheel hub
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
- F04D29/282—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers the leading edge of each vane being substantially parallel to the rotation axis
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
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- 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
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- 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
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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)
Abstract
The present invention provides a kind of turbofan, it has the wheel hub (10) for linking with drive shaft and being driven in rotation, the cyclic annular shield (11) of air suction inlet is configured and formed in opposite directions with wheel hub (10), and both ends are incorporated into the leading edge (13) of between wheel hub (10) and shield (11) and inner circumferential side and are configured at the more blades (12) of direction of rotation side relative to the rear (14) of peripheral side, wherein, about more blades (12), rear (14) is relative to the engaging portion (17) with wheel hub (10) and shield (11), (18) concavity (14A) is set as to anti-airflow direction.
Description
Technical field
The present invention relates to a kind of turbine wind that will be blown out from shroud along the air axially sucked to radial change direction
Fan and used the air-conditioning of the turbofan.
Background technique
Turbofan is by the wheel hub driven by rotations such as motors, the shield configured in opposite directions with the wheel hub and is configured at wheel hub
More blades between shield are constituted.About the blade of the turbofan, between wheel hub and shield, the end of inner circumferential side is
Leading edge is configured at that the case where more leaning on direction of rotation side than the end of peripheral side i.e. rear is more, and is shaped to wing section shape
Situation is more, but because by being limited on forming, section shape is usually along axial identical two-dimensional shapes (for example, ginseng
Examine patent document 1 etc.).But nowadays, manufacturing method is gradually unrestricted, it was also proposed that has blade being set as three-dimensional shaped along axial direction
The kinds of schemes such as shape or the turbofan for being set as hollow shape (for example, referenced patent document 2-4 etc.).
On the other hand, low-noise and efficiently to turn to target and pay attention to the turbofan of performance, for example, such as patent document
Shown in 5-7, proposition has to inhibit generated U-vortex in the engaging portion of wheel hub and blade, and is set as the wheel of blade
The curved structure of opposite direction near the leading edge of hub side to direction of rotation or direction of rotation, to form U-vortex suppressing portion
Turbofan and space is reduced in order to form dead water region between blade and shield, and by a part of blade to rotation side
To opposite direction bending, and the turbofan connected via the arc surface of the bending part and shield, or by the wheel of trailing edge
The lateral direction of rotation of hub and the bending of the two directions of the opposite direction of direction of rotation, can speed up gas in the trailing edge potion of blade
The turbofan etc. of stream.
That is, when for turbofan, since direction will be changed along the air flow direction radial direction axially sucked, from suction inlet
The air stream of outer edge side sucking can not be bent completely because of inertia force, and be easy to be biased to the fluid of hub side in internal become, connect
The position blade of nearly suction inlet can not be functioned effectively, so as to cause efficiency decline, and be generated in blowout side by air-flow
Deviation caused by high speed jet stream, or adverse current is generated near suction inlet, so that noise tends to get bigger.Also, work as turbine
When fan is suitable for air-conditioning, air and blowout side are being sucked by quadrangle from the quadrilateral shape access that have passed through grid and filter
It works under the nonaxisymmetrical pressure field that the heat exchanger of shape is surrounded, therefore spreads the span direction (axial direction) of entire fan, it is difficult
It is such as above-mentioned to realize identical fluid, propose have with the low-noise and efficient various schemes for turning to target.
Conventional art document
Patent document
Patent document 1: Japanese Unexamined Patent Publication 2002-235695 bulletin
Patent document 2: Japanese Unexamined Patent Publication 2007-170331 bulletin
Patent document 3: Japanese Unexamined Patent Publication 2007-170771 bulletin
Patent document 4: Japanese Unexamined Patent Publication 2010-216486 bulletin
Patent document 5: Japanese Unexamined Patent Publication 2009-127541 bulletin
Patent document 6: International Publication No. 2009/069606
Patent document 7: International Publication No. 2010/128618
Summary of the invention
The invention technical task to be solved
In aforementioned turbofan and the air-conditioning for having used the turbofan, when driving force, that is, fan of turbofan is defeated
When entering power and being set as evaluation parameter, room for improvement is still remained in turbofan.That is, it is eternal for reducing fan input power
Project considers from the viewpoint, has carried out fluid analysis to turbofan by finite volume method, result is specified current
In turbofan, in the suction surface of the peripheral side (rear side) of blade, the air stream existed along blade is easy to remove from aerofoil
Trend on the other hand in the pressure surface side of blade, generate high static pressure region, so that the air stream along blade slows down and (generates drive
The loss of power), fan efficiency decline.
The present invention is to complete in light of this situation, the peripheral side that its purpose is to provide a kind of by inhibiting blade
The removing of air stream in the suction surface of (rear side), and inhibit the deceleration of the air stream in the pressure surface side of blade, it can
It improves fan efficiency and the driving force i.e. turbofan of fan input power of fan can be reduced and used the turbofan
Air-conditioning.
For solving the means of technical task
In order to solve the above problems, turbofan of the invention and the air-conditioning of the turbofan has been used to use with lower section
Method.
That is, the 1st aspect of the present invention provides a kind of turbofan, which is characterized in that have: wheel hub drives with motor
Axis links and is driven in rotation；Cyclic annular shield configures in opposite directions with the wheel hub, and forms air suction inlet；And more blades,
Its both ends is incorporated between the wheel hub and the shield, and the leading edge of inner circumferential side is configured at rotation relative to the rear of peripheral side
Turn direction side, about the more blades, the rear relative to the engaging portion of the wheel hub and the shield to anti-air
Stream direction is set as concavity.
According to the method, the rears (also referred to as rear line) of more blades is relative to the engaging portion with wheel hub and shield to anti-
Airflow direction is set as concavity, therefore is set as turbine linear and that convex is set as to airflow direction with by the rear line of blade
Fan is compared, and can be improved the removing of the air stream in the negative pressure surface side of blade and is able to suppress the disorder of air stream, and lead to
Generated high static pressure region in the positive pressure surface side for reducing blade is crossed, inhibits the deceleration (loss of driving force) of air stream and improves
Fan efficiency, so as to reduce the driving force (fan input power) of fan.I.e., which is because, by will be after blade
Edge line is set as concavity to anti-airflow direction, and the original shape of radius ratio for being set as concave region becomes smaller, when with same rotational speed
When rotary fan, the pressure rising by the air stream of fan can be reduced, is especially easy as a result, in shroud in suction surface
The position of removing, the pressure (static pressure) near trailing edge is reduced, therefore becomes easy flowing as air stream, so as to press down
System removing, on the other hand, in pressure surface, the influence for being biased to hub side by the air stream of fan is significant, the pressure of blade surface
Power also shows the distribution steeply risen towards hub side, but by the way that rear line is set as concavity, it is attached can to reduce trailing edge
Close pressure (static pressure), and the static pressure in pressure surface can be reduced, fan efficiency is improved, to reduce fan input power.Cause
This, can be realized the further efficient, low-noise of turbofan.
Also, in above-mentioned turbofan, the rear about the blade, the span side of the blade can be set as
To center portion in the range of the 25%~75% of the span direction, be set as concavity to anti-airflow direction as previously described.
According to the method, the center portion of the rear line of blade in the range of the 25~75% of the span direction of blade to
Anti- airflow direction is set as concavity, therefore will not influence function, the performance of the engaging portion of blade and wheel hub and shield, and can incite somebody to action
Blade is in conjunction with wheel hub and shield.Therefore, air stream will not be upset in the hub side engaging portion of blade and shroud engaging portion,
It is low-noise, efficient so as to realize.
Moreover, in above-mentioned any turbofan, the rear of the blade can be set as to anti-airflow direction
Concavity amount (with-indicate) relative to outer diameter fan D be set as -0.0142D~-0.0153D range.
According to the method, concavity amount from the rear line of blade to anti-airflow direction (with-indicate) relative to fan outside
Diameter D is set as -0.0142D~-0.0153D range, therefore can reduce the driving force of turbofan, that is, fan input power
For preferred scope.It therefore, can be efficient, low-noise by turbofan.
Moreover, in above-mentioned any turbofan, can be set as the leading edge of the blade relative to the wheel
The engaging portion of hub and the shield is set as concavity to airflow direction or is set as convex to anti-airflow direction.
According to the method, the leading edge (also referred to as costa) of blade is relative to the engaging portion with wheel hub and shield to air stream
Direction is set as concavity or is set as convex to anti-airflow direction, therefore by the way that costa to be displaced to airflow direction with concavity,
And sometimes, air stream will appear small disorder in the suction surface of blade, but can reduce the high static pressure region in positive pressure surface side
And inhibit the deceleration of air stream, and on the other hand, by the way that costa is displaced to anti-airflow direction with convex, and pressure surface sometimes
High static pressure region in side slightly becomes larger and the deceleration inhibitory effect of air stream slightly declines, but is able to suppress the sky in suction surface
The disorder of air-flow and inhibit to remove.That is, by the way that the costa of blade is set as concavity, the air stream side of blade to airflow direction
It shortens to length, the friction loss of air stream and blade surface is reduced, so as to reduce fan input power.But it is if recessed
Shape is excessively recessed, then the length of blade relative to the airflow direction of the distance between adjacent blade excessively shortens, and makes blade
It can deteriorate.Also, by the way that the costa of blade is set as convex to anti-airflow direction, usual air stream and blade surface rub
Mistake of wearing increases, on the other hand, the airflow direction length of practical blade, therefore by that will be flowed into from blade upstream side
Fluid stable guide to downstream side, inhibit the peak value of the static pressure on blade surface and fluid made to be difficult to remove, so as to
Fan input power is reduced, and can reduce fan noise.Therefore, fan input also can be sufficiently reduced in this case
Power can be realized the efficient and low-noise of turbofan.
Moreover, the leading edge of the blade can be set as to the concavity amount of airflow direction in above-mentioned turbofan
(with+indicate) range of 0.0091D~0.0153D is set as relative to outer diameter fan D, to the convex amount of anti-airflow direction
(with-indicate) relative to outer diameter fan D it is set as -0.0438D.
According to the method, concavity amount from costa to airflow direction (with+indicate) be set as relative to outer diameter fan D
The range of 0.0091D~0.0153D, to anti-airflow direction convex amount (with-indicate) be set as relative to outer diameter fan D-
0.0438D, therefore the driving force of turbofan, that is, fan input power can be reduced to preferred scope, thereby, it is possible to by whirlpool
It is efficient, low-noise to take turns fan.
Moreover, it can be set as the leading edge about the blade in above-mentioned any turbofan, the blade
The center portion in span direction is set as to airflow direction in this way in the range of the 25%~75% of the span direction
Concavity is set as convex to anti-airflow direction.
According to the method, the center portion of the costa of blade is in the range of the 25%~75% of the span direction of blade
Concavity is set as to airflow direction or is set as convex to anti-airflow direction, therefore will not influence the knot of blade and wheel hub and shield
Function, the performance in conjunction portion, and can be by blade in conjunction with wheel hub and shield.Therefore, in the hub side engaging portion of blade and shield
Air stream will not be upset in the engaging portion of side and can be realized low-noise, efficient.
Moreover, can be set in above-mentioned any turbofan: the engaging portion of the blade and the wheel hub is set as edge
The engaging portion of the smooth flexure plane of the opposite direction of direction of rotation, the blade and the shield is set as smooth along direction of rotation
Flexure plane.
According to the method, the engaging portion of blade and wheel hub is set as the flexure plane smooth along the opposite direction of direction of rotation, leaf
The engaging portion of piece and shield is set as the flexure plane smooth along direction of rotation, therefore by the way that the engaging portion of blade and wheel hub is set as edge
The smooth flexure plane of the opposite direction of direction of rotation, engaging portion is set as it is left-right asymmetry, so as to inhibit in engaging portion
The stagnation of air stream, on the other hand, by the way that the engaging portion of blade and shield to be set as to the flexure plane smooth along direction of rotation, with the wing
Power inhibits the removing of the fluid in negative pressure surface side, so as to keep air stream smooth.Therefore, Blade Properties are improved, are further dropped
Low fan input power so as to realize high efficiency, and inhibits the disorder of air stream, low-noise so as to realize.
Moreover, can be set in above-mentioned turbofan: the engaging portion of the blade and the wheel hub is to direction of rotation
The flexure plane of opposite direction angle (with+indicate) relative to the blade 1 pitch angles θ be set as 0.0563 θ~
The range of 0.0972 θ, with flexure plane from the engaging portion of the shield to direction of rotation angle (with-indicate) relative to described
1 pitch angles θ of blade is set as the range of -0.0154 θ of θ~-0.0972.
According to the method, opposite direction from the engaging portion of blade and wheel hub to direction of rotation flexure plane angle (with+come
Indicate) range of the θ of 0.0563 θ~0.0972 is set as relative to 1 pitch angles θ of blade, with the engaging portion of shield to rotation
The flexure plane in direction angle (with-indicate) be set as -0.0154 θ's of θ~-0.0972 relative to 1 pitch angles θ of blade
Range, therefore the stagnation for the air stream being able to suppress in hub side engaging portion, and the sky in negative pressure surface side is inhibited with wing power
The removing of air-flow, so as to further increase Blade Properties.Therefore, the driving force of turbofan, that is, fan input power is dropped
Low is preferred scope, so as to which turbofan is efficient, low-noise.
Moreover, can be set in above-mentioned any turbofan: the engaging portion of the blade and the wheel hub is set as edge
The engaging portion of the smooth flexure plane in direction of rotation, the blade and the shield is set as smooth along the opposite direction of direction of rotation
Flexure plane.
According to the method, the engaging portion of blade and wheel hub is set as the flexure plane smooth along direction of rotation, blade and shield
Engaging portion is set as the flexure plane smooth along the opposite direction of direction of rotation, therefore by the way that the engaging portion of blade and wheel hub is set as edge
The smooth flexure plane of the opposite direction of direction of rotation, engaging portion is set as it is left-right asymmetry, so as to inhibit in engaging portion
The stagnation of air stream.Also, by the way that the engaging portion of blade and shield to be set as to the flexure plane smooth along direction of rotation, keep shield attached
Air stream in close negative pressure surface side is smooth, so as to inhibit to remove.Therefore, Blade Properties are improved, fan is further decreased
Input power so as to realize high efficiency, and inhibits the disorder of air stream, low-noise so as to realize.
Moreover, can be set in above-mentioned turbofan: the engaging portion of the blade and the wheel hub is to direction of rotation
Flexure plane angle (with-indicate) be set as -0.0768 θ relative to 1 pitch angles θ of the blade, with the shield
Opposite direction from engaging portion to direction of rotation flexure plane angle (with+indicate) 1 pitch angle relative to the blade
Degree θ is set as 0.0031 θ.
According to the method, flexure plane from the engaging portion of blade and the wheel hub to direction of rotation angle (with-indicate)
1 pitch angles θ relative to the blade is set as -0.0768 θ, with the engaging portion of the shield to the phase negative side of direction of rotation
To flexure plane angle (with+indicate) be set as 0.0031 θ relative to 1 pitch angles θ of the blade, therefore can press down
The stagnation of air stream in hub side engaging portion processed, and inhibit the removing of the air stream in the negative pressure surface side near shield, from
And Blade Properties can be further increased.Therefore, the driving force of turbofan, that is, fan input power is reduced to preferred scope,
So as to which turbofan is efficient, low-noise.
Also, in above-mentioned any turbofan, can be set to: the engaging portion of the blade and the wheel hub is set as edge
The engaging portion of the smooth flexure plane in direction of rotation, the blade and the shield is set as the flexure plane smooth along direction of rotation.
According to the method, the engaging portion of blade and wheel hub is set as the flexure plane smooth along direction of rotation, blade and shield
Engaging portion is set as the flexure plane smooth along direction of rotation, therefore by being set as the engaging portion of blade and wheel hub along direction of rotation
The smooth flexure plane of opposite direction, engaging portion is set as it is left-right asymmetry, so as to inhibit stopping for the air stream in engaging portion
It is stagnant, on the other hand, by the way that the engaging portion of blade and shield to be set as to the flexure plane smooth along direction of rotation, inhibit negative with wing power
The removing of fluid in pressure surface side, so as to keep air stream smooth.Therefore, Blade Properties are improved, it is defeated to further decrease fan
Enter power, so as to realize high efficiency, and inhibits the disorder of air stream, it is low-noise so as to realize.
Moreover, can be set in above-mentioned turbofan: the engaging portion of the blade and the wheel hub is to direction of rotation
Flexure plane angle (with-indicate) be set as -0.0154 θ relative to 1 pitch angles θ of the blade, with the shield
Flexure plane from engaging portion to direction of rotation angle (with-indicate) relative to the blade 1 pitch angles θ be set as-
0.0461θ。
According to the method, flexure plane from the engaging portion of blade and wheel hub to direction of rotation angle (with-indicate) it is opposite
Be set as -0.0154 θ in 1 pitch angles θ of blade, with flexure plane from the engaging portion of shield to direction of rotation angle (with-come
Indicate) 1 pitch angles θ air stream for being set as -0.0461 θ, therefore being able to suppress in hub side engaging portion relative to blade
Stagnation, and inhibit with wing power the removing of the air stream in negative pressure surface side, so as to further increase Blade Properties.Cause
This, is reduced to preferred scope for the driving force of turbofan, that is, fan input power, so as to which turbofan is efficient, low
Noise.
Moreover, the 2nd aspect of the present invention provides a kind of air-conditioning, which is characterized in that have: pressure fan sucks Interior Space
Gas and blow out；And heat exchanger, the either side being configured in the suction side or blowout side of the pressure fan, and to the Interior Space
Gas is cooled down or is heated, and the pressure fan is set as above-mentioned any turbofan.
It according to the method, sucks room air and is simultaneously cooled down or heated by heat exchanger, and to the indoor blowout temperature adjustment
The pressure fan of wind is set as above-mentioned any turbofan, therefore reduces driving force, that is, fan input power of turbofan, from
And it can be realized the efficient, low-noise of turbofan.It therefore, can be by the further high performance of air-conditioning and low-noise.
Invention effect
Turbofan according to the present invention can improve the removing of the air stream in the negative pressure surface side of blade, and can press down
The disorder of air stream processed, and generated high static pressure region in the positive pressure surface side of blade is reduced, and inhibit the deceleration of air stream
(loss of driving force) can reduce the driving force (fan input power) of fan, therefore energy thus, it is possible to improve fan efficiency
Enough realize the further efficient, low-noise of turbofan.
Air-conditioning according to the present invention, can reduce the driving force i.e. fan input power of turbofan, and can be realized whirlpool
The efficient, low-noise of fan is taken turns, therefore air-conditioning can be reached to higher performance and low-noise.
Detailed description of the invention
Fig. 1 is the exploded perspective view of air-conditioning involved in one embodiment of the present invention.
Fig. 2 is the fan-shaped (A) for indicating the turbofan being applicable in aforementioned air-conditioning, the limit stream on its blade surface
The figure of static pressure isopleth (C) on line (B) and blade surface.
Fig. 3 is used turbofan shape when carrying out fluid analysis to aforementioned turbofan by finite volume method
The comparison figure of (A) to (E).
Fig. 4 is the comparison figure of the limiting streamline (A) to (E) on the blade surface of aforementioned each turbofan.
Fig. 5 is the comparison figure of the static pressure isopleth (A) to (E) on the blade surface of aforementioned each turbofan.
Fig. 6 is the displacement shape relative to the original shape (A) of the blade inlet edge for the design variable for being used as aforementioned each turbofan
The comparison figure of shape (B), (C).
Fig. 7 is the displacement shape relative to the original shape (A) of the trailing edge for the design variable for being used as aforementioned each turbofan
The comparison figure of shape (B), (C).
Fig. 8 is the original shape relative to the blade wheel hub lateral bend shape for the design variable for being used as aforementioned each turbofan
(A) the comparison figure of displacement shape (B), (C).
Fig. 9 is the original shape relative to the blade shroud lateral bending curved shape for being used as the design variable for indicating aforementioned each turbofan
The comparison figure of the displacement shape (B) of shape (A), (C).
Figure 10 is the blade 2 integrally rotated around rotating shaft center using the blade for the design variable for making aforementioned each turbofan
The coincidence pattern of piece part.
Figure 11 is 2 parts of the leading edge for indicating the blade of the design variable as aforementioned each turbofan and the displacement of rear
Coincidence pattern.
Figure 12 is the leading edge of the blade for the design variable that explanation is used as aforementioned each turbofan and the displacement state of rear
Explanatory diagram.
Figure 13 is the schematic diagram for illustrating the wing power of aforementioned each turbofan.
Figure 14 is to indicate the table of design variable (A) and objective function (B) used in the analysis of aforementioned each turbofan
Lattice.
Figure 15 is the table for indicating the design variable value in the analysis result based on aforementioned finite volume method.
Figure 16 is to indicate that objective function D'(corresponds to the ratio between air quantity power and original value) comparison result bar chart.
Figure 17 is the chart for indicating the correlativity of objective function D' and design variable (1).
Figure 18 is the chart for indicating the correlativity of objective function D' and design variable (2).
Figure 19 is the chart for indicating the correlativity of objective function D' and design variable (3).
Figure 20 is the chart for indicating the correlativity of objective function D' and design variable (4).
Specific embodiment
Hereinafter, being illustrated using Fig. 1 to Figure 20 to one embodiment of the present invention.
The exploded perspective view of air-conditioning involved in one embodiment of the present invention is shown in FIG. 1.
Air-conditioning 1 involved in present embodiment is set as ceiling embedded type air conditioner 1, but the present invention is not limited to the smallpoxes
Plate embedded type air conditioner 1 can also be suitable for the air-conditioning 1 of other patterns certainly.
The ceiling embedded type air conditioner 1 has the unit for the substantially quadrilateral shape that ceiling is set to by suspensions such as bolts
Main body 2, the quadrilateral shape for being set to below the unit main body 2 and having indoor air sucting inlet 4 and tempering air blow-off outlet 5
Ceiling panel 3, the loudspeaker in unit main body 2 is configured in the mode opposite with the indoor air sucting inlet 4 of ceiling panel 3
Mouth 6, the turbofan (pressure fan) 7 that the top plate of unit main body 2 is fixedly installed in the mode opposite with horn mouth 6 and with
The mode for surrounding turbofan (pressure fan) 7 is set to heat exchanger 8 of quadrilateral shape in unit main body 2 etc..
Turbofan 7 is the motor 9 for having the top plate for being fixedly installed on unit main body 2, in conjunction with the rotary shaft 9A of motor 9
And by the wheel hub (mainboard) 10 of the rotation driving of motor 9, the cyclic annular shield (side plate) 11 configured in opposite directions with wheel hub (mainboard) 10 and
The more blades 12 being arranged in such a way that both ends are combined with wheel hub (mainboard) 10 and shield (side plate) 11 respectively without shell structure
Fan.About the more blades 12 of the turbofan 7, leading edge (the otherwise referred to as costa of inner circumferential side.) 13 with relative to
Rear (the otherwise referred to as rear line of peripheral side.) 14 be located at the side direction of rotation N modes configure.
As shown in Fig. 2 (A), the turbofan 7 of present embodiment sets the shape of blade 12 in a manner of aftermentioned
It counts, as a result, the limiting streamline as shown in Fig. 2 (B) (with the fluid of linear visualization blade surface), by the suction surface 15 of blade 12
Air stream in side is set as the clearly streamline of the change dramatically less (not removing) at interval, and quiet as shown in Fig. 2 (C)
Isogram is pressed, the static pressure in 16 side of pressure surface of blade 12 is set as eliminating or reduce to the minimum high static pressure region and inhibits air
The deceleration (loss) of stream, to reduce the driving force i.e. fan input power of turbofan 7.
In the present embodiment, in order to by the driving force of turbofan 7, that is, fan input power as a parameter to turbine
The performance of fan 7 is evaluated, and is divided with the state that turbofan 7 is mounted in air-conditioning 1 by finite volume method
Analysis, and the shape that result sets blade 12 is analyzed according to it.In order to carry out the fluid analysis, as shown in Figure 14 (A), by (1) leaf
The displacement (amount of movement) of the leading edge 13 of piece 12, the displacement (amount of movement) of the rear 14 of (2) blade 12, (3) blade 12 hub side
The bending (rotation angle) this 4 of the shroud engaging portion 18 of the bending (rotation angle) and (4) blade 12 of engaging portion 17 is used as design
Variable evaluates the Parameter analysis of 41 examples.Moreover, with the 1st shape (No.31) in the Parameter analysis for base
Plinth has found out optimum shape (No.59).
Fig. 2 (A) and Fig. 3 (A) to Fig. 3 (E) is to show the fan (No.59) of optimum shape；It is evaluated in Parameter analysis
In 41 examples, it is evaluated as the fan of 1 (No.31), 2 (No.32) and 3 (No.06)；Original-shape as evaluation criteria
Fan (No.0)；And it is evaluated as the figure of the shape of the fan (No.14) of last position (41).Fig. 2 (A) and Fig. 3 (A) extremely
The detail shape of fan shown in Fig. 3 (E) will be aftermentioned, but the fan of original-shape is set as such as flowering structure: as shown in Fig. 3 (D),
The section of blade 12 is in along axial identical two-dimensional shapes, and the costa 13 and rear line 14 of blade 12 are straight in being parallel to each other
Line, the hub side engaging portion 17 and shroud engaging portion 18 that the both ends of blade 12 are combined with wheel hub 10 and shield 11 are relative to wheel
Hub 10 and shield 11 substantially at right angles to combine.
Also, it is evaluated as 41 and the fan-shaped of minimum example No.14 is set as such as flowering structure: as shown in Fig. 3 (E),
Relative to fan-shaped original shown in Fig. 3 (D), the costa 13 of blade 12 is set as concavity 13A to airflow direction, it will
Rear line 14 is set as convex 14B to airflow direction, and hub side engaging portion 17 is set as the opposite direction to direction of rotation
Shroud engaging portion 18 is set as to the curved flexure plane 18A of the opposite direction of direction of rotation by curved flexure plane 17A.
Moreover, being shown into (E) shown in (A) to (E) that compares with Fig. 3 in (A) to (E) of Fig. 4 and (A) of Fig. 5
The limiting streamline of the corresponding each fan of fan-shaped and the figure of static pressure isopleth.
Here, being described in detail according to shape, structure of the Fig. 6 to Fig. 9 to 4 design variables (1)~(4) above-mentioned.
(1) displacement (amount of movement) of the leading edge 13 of blade 12 indicates: as shown in fig. 6, relative to by the leading edge 13 of blade 12
It is set as original-shape shown in linear Fig. 6 (A), as shown in Fig. 6 (B), costa 13 is set as relative to wheel hub 10 and shield
Concavity 13A that the engaging portion 17 and 18 of cover 11 is recessed to airflow direction (by amount of movement with+indicate), or such as Fig. 6 (C) institute
Show, the convex 13B that is set as expanding to anti-airflow direction (by amount of movement with-indicate).
(2) displacement (amount of movement) of the rear 14 of blade 12 indicates: as shown in fig. 7, relative to by the rear 14 of blade 12
It is set as original-shape shown in linear Fig. 7 (A), as shown in Fig. 7 (B), rear line 14 is set as relative to wheel hub 10 and shield
Concavity 14A that the engaging portion 17 and 18 of cover 11 is recessed to anti-airflow direction (by amount of movement with-indicate), or such as Fig. 7 (C) institute
Show, the convex 14B that is set as expanding to airflow direction (by amount of movement with+indicate).
(3) bending (rotation angle) of the hub side engaging portion 17 of blade 12 indicates: as shown in figure 8, relative to by blade 12
Hub side engaging portion 17 with original-shape, such as Fig. 8 shown in Fig. 8 (A) in conjunction with the mode substantially rectangular with 10 side of wheel hub
(B) shown in, the hub side engaging portion 17 of blade 12 is set as curved curved to the opposite direction (counter clockwise direction) of direction of rotation
When curved surface 17A relative to the rotation angle of wheel hub 10 (by rotation angle with+indicate), or as shown in Fig. 8 (C), be set as to rotation side
When flexure plane 17B curved to (clockwise direction) relative to the rotation angle of wheel hub 10 (by rotation angle with-indicate).
(4) bending (rotation angle) of the shroud engaging portion 18 of blade 12 indicates: as shown in figure 9, relative to by blade 12
Shroud engaging portion 18 with original-shape, such as Fig. 9 shown in Fig. 9 (A) in conjunction with the mode substantially rectangular with 11 side of shield
(B) shown in, the shroud engaging portion 18 of blade 12 is set as curved curved to the opposite direction (counter clockwise direction) of direction of rotation
When curved surface 18A with the rotation angle of shield 11 (by rotation angle with+indicate), or as shown in Fig. 9 (C), be set as (suitable to direction of rotation
Clockwise) curved flexure plane 18B when with the rotation angle of shield 11 (by rotation angle with-indicate).
In addition, the engaging portion 17,18 about blade 12 and wheel hub 10 and shield 11, as shown in Figure 10, by blade entirety phase
It is curved for the opposite direction (counter clockwise direction) or direction of rotation (clockwise direction) of center O to the direction of rotation of rotary shaft 9A
Song, in case the angle between blade 12 and air stream changes.
Moreover, as shown in figure 11, the outer diameter direction of blade 12 is set as+direction, in the bending line (ridge of blade (wing) 12
Line) and its extended line on, the displacement (amount of movement) of the leading edge 13 and rear 14 that make blade 12 is to be concavely or convexly displaced.That is, such as
Shown in Figure 12, the leading edge 13 of blade 12 and the displacement of rear 14 are in 13 side of leading edge and this two sides of 14 side of rear in span direction
It is set as in the range of substantially 25%~the 75% of the blade height of (axial rotary) along bending line (crestal line) mobile identical amount
Concavely or convexly.Moreover, being set as the structure connected respectively with smooth curve in wheel hub 10 and shield 11.
Also, the diagram of the wing power BF about turbofan 7 is shown in FIG. 13.
The wing power BF of turbofan 7 is equivalent to the barometric gradient acted between the multi-disc wing (blade 12), and acts on for the wing
In fluid, that is, air stream power, as shown in figure 13, by tilting the wing (blade 12), becomes wing power BF and act on aerofoil in straight
The direction at angle.Wing power BF plays inhibition suction surface by the way that air stream is pressed to wall surface (being the wall surface of shield 11 in Figure 13)
The effect of the removing of side.
Hereinafter, according to above-mentioned item, to the blade 12 set in a manner of the fan input power for reducing turbofan 7
Shape, structure be described in detail.
[optimum shape fan (example No.59)]
Fig. 2 (A) is the perspective view for having the turbofan 7 of blade 12 for the optimum shape for being set as example No.59.
The blade 12 is set as costa 13 and is set as concavity 13A (with reference to Fig. 6 (B)) to airflow direction, and rear line 14 to
Anti- airflow direction is set as the structure of concavity 14A (with reference to Fig. 7 (B)).
Also, the engaging portion (hub side engaging portion) 17 for being set as blade 12 and wheel hub 10 is set as the phase negative side to direction of rotation
To (counter clockwise direction) curved flexure plane 17A (refer to Fig. 8 (B)), and blade 12 is with the engaging portion of shield 11 (in conjunction with shroud
Portion) 18 it is set as structure to direction of rotation (clockwise direction) curved flexure plane 18B (with reference to Fig. 9 (C)).In addition, about this
Hub side engaging portion 17 and shroud engaging portion 18, as shown in Figure 10, blade is whole to be bent relative to rotating shaft center O, in order to avoid
Angle between blade 12 and air stream changes.
Moreover, aforementioned costa 13 and rear line 14 are set as such as flowering structure: as shown in Figure 11, Figure 12, passing through blade 12
Span direction (axial rotary) center portion in the range of the 25~75% of span direction size, in blade (wing) 12
Mobile equal amount on bending line (crestal line) and its extended line, costa 13 are set as concavity 13A to airflow direction, rear line 14 to
Anti- airflow direction is set as concavity 14A.
It, will when the outer diameter of turbofan 7 is set as D [m] (with reference to Figure 10, Figure 12) in the blade 12 of the optimum shape
When 1 pitch angles of blade 12 are set as θ [°] (with reference to Figure 10), about previous designs variable (1) to (4), such as the table institute of Figure 15
Show, the displacement (amount of movement) of the leading edge (pull-LE) 13 of (1) blade 12 relative to airflow direction (with+indicate) be set as phase
When in the concavity 13A of 0.0153D, the displacement (amount of movement) of the rear (pull-TE) 14 of (2) blade 12 is relative to anti-air stream side
To (with-indicate) be set as being equivalent to the concavity 14A of -0.0153D.
Also, (3) opposite direction (inverse time of the bending (rotation angle) of the hub side engaging portion 17 of blade 12 to direction of rotation
Needle direction, with+indicate) it is set as the flexure plane 17A of 0.0972 θ, the bending (rotation of the shroud engaging portion 18 of (4) blade 12
Angle) to direction of rotation (clockwise, with-indicate) it is set as the flexure plane 18B of -0.0972 θ.
[fan-shaped of example No.31 (1)]
The perspective view for having the turbofan 7 of blade shape of example No.31 (1) is shown in Fig. 3 (A).
Identically as the blade 12 of optimum shape, which is set as costa 13 and is set as concavity 13A to airflow direction
(referring to Fig. 6 (B)), and rear line 14 is set as the structure of concavity 14A (with reference to Fig. 7 (B)) to anti-airflow direction.
Also, the engaging portion (hub side engaging portion) 17 for being set as blade 12 and wheel hub 10 is set as the phase negative side to direction of rotation
To (counter clockwise direction) curved flexure plane 17A (refer to Fig. 8 (B)), and blade 12 is with the engaging portion of shield 11 (in conjunction with shroud
Portion) 18 it is set as structure to direction of rotation (clockwise direction) curved flexure plane 18B (with reference to Fig. 9 (C)).In addition, about this
Hub side engaging portion 17 and shroud engaging portion 18, as shown in Figure 10, blade is whole to be bent relative to rotating shaft center O, in order to avoid
Angle between blade 12 and air stream changes.
Moreover, costa 13 and rear line 14 are set as such as flowering structure: as shown in FIG. 11 and 12, by blade 12 across
Center portion away from direction (axial rotary) is in the range of the 25~75% of span direction size, in the bending of blade (wing) 12
Mobile equal amount on line (crestal line) and its extended line, costa 13 are set as concavity 13A to airflow direction, and rear line 14 is to anti-sky
Airflow direction is set as concavity 14A.
In the blade 12 of example No.31 (1), about previous designs variable (1) to (4), as shown in the table of Figure 15,
(1) displacement (amount of movement) of the leading edge (pull-LE) 13 of blade 12 relative to airflow direction (with+indicate) be set as being equivalent to
The concavity 13A of 0.0153D, the displacement (amount of movement) of the rear (pull-TE) 14 of (2) blade 12 is relative to anti-airflow direction
(with-indicate) be set as being equivalent to the concavity 14A of -0.0153D.
Also, (3) opposite direction (inverse time of the bending (rotation angle) of the hub side engaging portion 17 of blade 12 to direction of rotation
Needle direction, with+indicate) it is set as the flexure plane 17A of 0.0563 θ, the bending (rotation of the shroud engaging portion 18 of (4) blade 12
Angle) to direction of rotation (clockwise, with-indicate) it is set as the flexure plane 18B of -0.0154 θ.
[fan-shaped of example No.32 (2)]
The perspective view for having the turbofan 7 of blade shape of example No.32 (2) is shown in Fig. 3 (B).
Identically as the blade 12 of optimum shape, which is set as costa 13 and is set as concavity 13A to airflow direction
(referring to Fig. 6 (B)), and rear line 14 is set as the structure of concavity 14A (with reference to Fig. 7 (B)) to anti-airflow direction.
On the other hand, be set as blade 12 and wheel hub 10 engaging portion (hub side engaging portion) 17 be set as it is (suitable to direction of rotation
Clockwise) curved flexure plane 17B (referring to Fig. 8 (C)), and the engaging portion (shroud engaging portion) 18 of blade 12 and shield 11
It is set as the structure to the curved flexure plane 18A of opposite direction (counter clockwise direction) (with reference to Fig. 9 (B)) of direction of rotation.In addition, closing
In the hub side engaging portion 17 and shroud engaging portion 18, as shown in Figure 10, blade is whole to be bent relative to rotating shaft center O,
In order to avoid the angle between blade 12 and air stream changes.
Moreover, costa 13 and rear line 14 are set as such as flowering structure: as shown in FIG. 11 and 12, by blade 12 across
Center portion away from direction (axial rotary) is in the range of the 25~75% of span direction size, in the bending of blade (wing) 12
Mobile equal amount on line (crestal line) and its extended line, costa 13 are set as concavity 13A to airflow direction, and rear line 14 is to anti-sky
Airflow direction is set as concavity 14A.
In the blade 12 of example No.32 (2), about previous designs variable (1) to (4), as shown in the table of Figure 15,
(1) displacement (amount of movement) of the leading edge (pull-LE) 13 of blade 12 relative to airflow direction (with+indicate) be set as being equivalent to
The concavity 13A of 0.0091D, the displacement (amount of movement) of the rear (pull-TE) 14 of (2) blade 12 is relative to anti-airflow direction
(with-indicate) be set as being equivalent to the concavity 14A of -0.0142D.
Also, the bending (rotation angle) of the hub side engaging portion 17 of blade 12 (3) to direction of rotation (clockwise,
With-indicate) be set as the flexure plane 17B of -0.0768 θ, the bending (rotation angle) of the shroud engaging portion 18 of the blade 12 of (4) to
The opposite direction (counterclockwise, with+indicate) of direction of rotation is set as the flexure plane 18A of 0.0031 θ.
[fan-shaped of example No.06 (3)]
The perspective view for having the turbofan 7 of blade shape of example No.06 (3) is shown in Fig. 3 (C).
The blade 12 is set as costa 13 and is set as convex 13B (with reference to Fig. 6 (C)) to anti-airflow direction, and rear line 14
The structure of concavity 14A (with reference to Fig. 7 (B)) is set as to anti-airflow direction.
On the other hand, be set as blade 12 and wheel hub 10 engaging portion (hub side engaging portion) 17 be set as it is (suitable to direction of rotation
Clockwise) curved flexure plane 17B (referring to Fig. 8 (C)), and the engaging portion (shroud engaging portion) 18 of blade 12 and shield 11
It is set as the structure to the curved flexure plane 18B of opposite direction (counter clockwise direction) (with reference to Fig. 9 (C)) of direction of rotation.In addition, closing
In the hub side engaging portion 17 and shroud engaging portion 18, as shown in Figure 10, blade is whole to be bent relative to rotating shaft center O,
In order to avoid the angle between blade 12 and air stream changes.
Moreover, costa 13 and rear line 14 are set as such as flowering structure, as shown in FIG. 11 and 12, by blade 12 across
Center portion away from direction (axial rotary) is in the range of the 25~75% of span direction size, in the bending of blade (wing) 12
Mobile equal amount on line (crestal line) and its extended line, costa 13 are set as convex 13B to anti-airflow direction, and rear line 14 is to anti-
Airflow direction is set as concavity 14A.
In the blade 12 of example No.06 (3), about previous designs variable (1) to (4), as shown in the table of Figure 15,
(1) displacement (amount of movement) of the leading edge (pull-LE) 13 of blade 12 to anti-airflow direction (with-indicate) be set as being equivalent to-
The convex 13B of 0.0438D, the displacement (amount of movement) of the rear (pull-TE) 14 of (2) blade 12 is relative to anti-airflow direction
(with-indicate) be set as being equivalent to the concavity 14A of -0.0153D.
Also, the bending (rotation angle) of the hub side engaging portion 17 of blade 12 (3) to direction of rotation (clockwise,
With-indicate) be set as the flexure plane 17B of -0.0154 θ, the bending (rotation angle) of the shroud engaging portion 18 of the blade 12 of (4) to
Direction of rotation (clockwise, with-indicate) is set as the flexure plane 18B of -0.0461 θ.
In addition, the original blade shape about example No.0, as shown in the table of Figure 15,4 design variables (1) to (4)
It is set as 0.Also, about the blade shape for evaluating minimum (41) example No.14, (1) is by the leading edge (pull- of blade 12
LE) 13 displacement (amount of movement) to airflow direction (with+indicate) be set as being equivalent to the concavity 13A of 0.0153D, and (2) will
The displacement (amount of movement) of rear (pull-TE) 14 relative to airflow direction (with+indicate) be set as being equivalent to the convex of 0.0438D
Shape 14B, (3) by opposite direction from the bending (rotation angle) of the hub side engaging portion 17 of blade 12 to direction of rotation (with+carry out table
Show) be set as the flexure plane 17A of 0.0563 θ, and (4) by the bending (rotation angle) of shroud engaging portion 18 to the opposite of direction of rotation
Direction (with+indicate) it is set as 0.0358 flexure plane 18A.
By structure described above, according to the present embodiment, following function and effect are played.
In aforementioned turbofan 7 and air-conditioning 1, by the rotation of turbofan 7 from the room air of ceiling panel 3
The room air that suction inlet 4 sucks is inhaled into from the opening portion of 11 side of shield of turbofan 7 along axial direction via horn mouth 6.It inhales
The air circulation entered to turbofan 7 cross more blades 12 to it is radial change direction after be blown out, and by surround whirlpool
It is cooled during the heat exchanger 8 that is arranged of mode of wheel fan 7 or heating, thus as tuning wind from ceiling panel 3
Four sides on set 4 temperature adjustment blow-off outlets 5 blow to it is indoor for the adjusting of indoor temperature.
When for turbofan 7, change direction for radial (centrifugal direction) is flowed to along the air axially sucked, therefore especially
The air stream that (11 side of shield) sucks near the outer rim of suction inlet becomes inclined because inertia force can not be bent completely inside fan
To the fluid of 10 side of wheel hub, nearside is being leaned on shield 11, blade 12 can not be functioned effectively, and efficiency declines, and
It blows out side and generates the high speed jet stream as caused by the deviation of air-flow, or generate adverse current in suction side, so that aerodynamic noise holds
Easily become larger.Also, when being suitable for air-conditioning 1, air is inhaled into from the air duct of quadrilateral shape, in the heat exchanger 8 by quadrilateral shape
The case where working in the nonaxisymmetrical pressure field surrounded is more, it is difficult to realize throughout the span direction of entire fan identical
Fluid.
Therefore, turbofan 7 involved in present embodiment is by 4 projects of aforementioned (1) to (4) shown in Figure 14 (A)
It as design variable, will be carried out based on the fluid analysis of finite volume method with parameterizing, and according to the design variable value, setting
The shape of blade 12.In addition, showing the definition of objective function D' in Figure 14 (B).Also, in the list of Figure 15, summarize
Design variable value in analysis result based on finite volume method.
It is only shown in the list of earlier figures 15: the fan of the optimum shape of example No.59；The Parameter analysis of 41 examples
Middle evaluation high 1 (example No.31), 2 (example No.32) and 3 (example No.06) this 3 fans；As evaluation criteria
Original fan (example No.0)；And evaluate the result that 41 (example No.14) minimum fans amount to 6 examples.
Moreover, about preceding aim function D', the bar chart for comparing the value of aforementioned 6 examples is shown in Figure 16,
In Figure 17 into Figure 20, showing indicates objective function D' and design variable (1), objective function D' and design variable (2), target
The chart of function D' and design variable (3) and objective function D' and the correlativity of design variable (4).
It is clear that the turbofan 7 of present embodiment is set as such as flowering structure by these analysis results: such as Fig. 2 (A) or figure
Shown in 3 (A) to Fig. 3 (C), the center portion of the rear line 14 of more blades 12 at span direction (axial rotary) 25~75%
In the range of to anti-airflow direction be set as concavity 14A, therefore the air stream of 15 side of suction surface of blade 12 can be set as
The sharply change at limiting streamline shown in Fig. 2 (B) or Fig. 4 (A) to Fig. 4 (C) (with the fluid of linear visualization blade surface) interval
Change the clearly streamline of less (not removing).
That is, example No.0 original-shape and evaluate in example No.14 at last, such as Fig. 4 (D) and Fig. 4 (E)
Shown in limiting streamline, find the position X of the air stream disorder of 15 side of suction surface of blade 12, it is peeling-off in air stream, but
The optimum shape of the example No.59 shown in Fig. 2 (A) or Fig. 3 (A) to Fig. 3 (C) evaluates example No.31 at 1~3, thing
In example No.32 and example No.6, the position X without disorder in the limiting streamline of suction surface 15, it is known that the removing in suction surface 15
It is improved.
Also, static pressure (aerofoil pressure) is distributed in the pressure surface 16 of blade 12 by the rotation of turbofan 7, but its
Static pressure is higher or high static pressure region is bigger, and the air stream along blade 12 is more slowed down, and indicates that fan efficiency declines due to its loss.?
In the turbofan 7 of present embodiment, the static pressure isogram as shown in Fig. 2 (C) or Fig. 5 (A) to Fig. 5 (C), with Fig. 5 (D) and
Static pressure isogram shown in Fig. 5 (E) is compared, and pressure can be reduced to the high static pressure region or reduces region.
That is, example No.0 original-shape and evaluate in example No.14 at last, such as Fig. 5 (D) and Fig. 5 (E)
Shown, generated high static pressure region Y is occurred in the pressure surface 16 of blade 12 with biggish region Y, but in Fig. 2 (C) or Fig. 5
The optimum shape of example No.59 shown in (A) to Fig. 5 (C) or evaluation are at 1~3 example No.31, example No.32 and example
High static pressure region Y does not occur known in No.6, or becomes very small region Y, does not generate the deceleration of air stream, does not occur by subtracting
The case where loss caused by fast and fan efficiency decline.
In this way, improving the negative pressure of blade 12 by the way that the rear line 14 of blade 12 is set as concavity 14A to anti-airflow direction
The removing of air stream in 15 side of face so as to inhibit the disorder of air stream, and is distributed by reducing in 16 side of pressure surface
High static pressure region Y, inhibit the deceleration of air stream, to improve fan efficiency, as shown in Figure 16 and Figure 18, can reduce turbine
The driving force of fan 7, that is, fan input power.
The reason for this is that by the way that the rear line 14 of blade 12 is set as concavity 14A to anti-airflow direction, when being set as concavity
The original shape of radius ratio in region become smaller, and when rotating turbofan 7 with same rotational speed, can reduce through turbine wind
The pressure of the air stream of fan 7 rises, as a result, behind the position that suction surface 15 is especially easily peeled off in 11 side of shield, blade 12
Pressure (static pressure) near edge 14 is reduced, therefore becomes easy flowing as air stream, so as to inhibit to remove.
On the other hand, in pressure surface 16, the influence for being biased to 10 side of wheel hub by the air stream of turbofan 7 is significant, and
And the pressure on the surface of blade 12 also shows the distribution steeply risen towards 10 side of wheel hub, but recessed by the way that rear line 14 to be set as
Shape 14A can reduce the pressure (static pressure) near the rear 14 of blade 12, and can reduce the static pressure in pressure surface 16, therefore
It can be improved the fan efficiency of turbofan 7, so as to reduce fan input power, therefore, can be realized turbofan 7
It is further low-noise, efficient.
Also, it is because of the 25 of the center portion in span direction that rear line 14, which is set as concavity 14A to anti-airflow direction,
~75% range is preferable, will not influence function, performance with the engaging portion 17,18 of wheel hub 10 and shield 11, and can be by leaf
Piece 12 is combined with wheel hub 10 and shield 11.Therefore, air will not be upset in hub side engaging portion 17 and shroud engaging portion 18
Stream, it is low-noise, efficient so as to realize.
Moreover, when the outer diameter of turbofan 7 is set as D, by by the rear line 14 of blade 12 to anti-airflow direction
Concavity amount (with-indicate) be set as -0.0142D~-0.0153D range, as shown in Figure 16 and Figure 18, can be by turbine wind
Driving force, that is, fan input power of fan 7 is reduced to preferred scope.
On the other hand, in the turbofan 7 of present embodiment, about the costa 13 of blade 12, such as Fig. 2 (A) or Fig. 3
(A), shown in (B), by center portion in the range of the 25~75% of span direction (axial rotary) relative to wheel hub 10 and
The engaging portion 17 and 18 of shield 11 is set as concavity 13A to airflow direction, or as shown in Fig. 3 (C), is set as to anti-airflow direction
Convex 13B.
In this way, passing through the leaf by costa 13 to airflow direction with concavity 13A displacement, with optimum shape shown in Fig. 2
Piece 12 is compared, and as shown in Fig. 4 (B), air stream will appear small disorder in 15 side of suction surface of blade 12 sometimes, but with such as
High static pressure region that mode shown in Fig. 5 (B) reduces in 16 side of pressure surface and the deceleration for being able to suppress air stream, on the other hand,
By by costa 13 to anti-airflow direction with convex 13B displacement, as shown in Fig. 5 (C), the height in 16 side of pressure surface sometimes
Static pressure field slightly becomes larger, and the deceleration inhibitory effect of air stream slightly reduces, but inhibits negative in a manner of as shown in Fig. 4 (C)
The disorder of air stream in pressure surface 15 and be able to suppress removing.
This is because by the way that the costa 13 of blade 12 is set as concavity 13A, the air stream of blade 12 to airflow direction
Direction length shortens, and the friction loss on the surface of air stream and blade 12 is reduced, so as to reduce fan input power.But
It is that, if concavity 13A is excessively recessed, the length of blade of the airflow direction relative to the distance between adjacent blade 12 excessively becomes
It is short, and the performance of blade 12 is possible to deteriorate.Also, by the way that the costa 13 of blade 12 is set as convex to anti-airflow direction
The friction loss on the surface of 13B, usual air stream and blade 12 increases, on the other hand, the airflow direction of practical blade 12
Length, therefore by guiding the fluid stable flowed into from blade upstream side to downstream side, inhibit the surface of blade 12
On static pressure peak value and make fluid be difficult to remove, so as to reduce fan input power, and can reduce fan noise.
Therefore, in this embodiment, as shown in Figure 16, Figure 17 and Figure 18, also can be by the driving force of turbofan 7
Fan input power is reduced to preferred scope, so as to realize the efficient and low-noise of turbofan 7.
It, also will be in the costa 13 of blade 12 also, in this case, as shown in Fig. 2 (A) or Fig. 3 (A) to Fig. 3 (C)
Centre part is in the range of the 25~75% of span direction (axial rotary) relative to the engaging portion 17 with wheel hub 10 and shield 11
And 18 be set as concavity 13A to airflow direction, or is set as convex 13B to anti-airflow direction, therefore will not influence and wheel hub 10
And function, the performance of the engaging portion 17,18 of shield 11, and blade 12 can be combined with wheel hub 10 and shield 11.Therefore, it is taking turns
Air stream will not be upset in hub side engaging portion 17 and shroud engaging portion 18, it is low-noise, efficient so as to realize.
Also, in the costa 13 of blade 12 above-mentioned, by the concavity amount of the concavity 13A of airflow direction (with+come
Indicate) range of 0.0091D~0.0153D is set as relative to outer diameter fan D, it will be to the convex of the convex 13B of anti-airflow direction
Shape amount (with-indicate) it is set as -0.0438D relative to outer diameter fan D, therefore as shown in Figure 16 and Figure 18, it can by turbine wind
Driving force, that is, fan input power of fan 7 is reduced to preferred scope.Thereby, it is possible to turbofan 7 is low-noise, efficient.
Moreover, the turbofan 7 of present embodiment is set as the knot of blade 12 Yu wheel hub 10 as shown in Fig. 2 (A) and Fig. 3 (A)
Conjunction portion (hub side engaging portion) 17 is set as the flexure plane 17A smooth along the opposite direction of direction of rotation, and blade 12 and shield 11
Engaging portion (shroud engaging portion) 18 be set as the structure along the smooth flexure plane 18B in direction of rotation.
In this way, by the way that the engaging portion 17 of blade 12 and wheel hub 10 is set as the bending smooth along the opposite direction of direction of rotation
Face 17A, the engaging portion 17 with wheel hub 10 is set as it is left-right asymmetry, so as to inhibit stopping for the air stream in the engaging portion 17
It is stagnant, and by the way that the engaging portion of blade 12 and shield 11 is set as the flexure plane 18B smooth along direction of rotation, with wing power BF inhibition
The removing of fluid, so as to keep air stream smooth.Meanwhile as shown in Fig. 2 (B) and Fig. 4 (A), it is able to suppress the negative of blade 12
The disorder of air stream in 15 side of pressure surface, and as shown in Fig. 2 (C) and Fig. 5 (A), by 16 side of pressure surface for reducing blade 12
In high static pressure region and be able to suppress the deceleration (loss of driving force) of air stream.
Therefore, the Blade Properties for improving turbofan 7 can reduce turbofan 7 as shown in Figure 16, Figure 19 and Figure 20
Driving force, that is, fan input power, to realize high efficiency, and inhibit the disorder of air stream, so as to realize low noise
Change.
Also, it in the present embodiment, is set as the engaging portion (hub side engaging portion) 17 of blade 12 and wheel hub 10 to rotation
Turn the flexure plane 17A of the opposite direction in direction angle (with+indicate) be set as relative to 1 pitch angles θ of blade 12
The range of the θ of 0.0563 θ~0.0972, and by the flexure plane with the engaging portion of shield 11 (shroud engaging portion) 18 to direction of rotation
18B angle (with-indicate) relative to blade 1 pitch angles θ be set as -0.0154 θ of θ~-0.0972 range knot
Structure.
Therefore, it is able to suppress the stagnation of the air stream in the hub side engaging portion 17 of blade 12, and is inhibited with wing power
The removing of air stream in 15 side of suction surface, so that the performance of blade 12 is further increased, as a result, such as Figure 16, Figure 19 and Figure 20
It is shown, it is reduced to preferred scope also by by the driving force of turbofan 7, that is, fan input power, it can be high by turbofan 7
It is effectization, low-noise.
In addition, the present invention is not limited to be invented involved in aforementioned embodiments, in range without departing from the spirit,
It is able to carry out appropriate deformation.For example, in the foregoing embodiment, the day of heat exchanger 8 is equipped with to the blowout side in turbofan 7
The example being applicable in card embedded type air conditioner 1 is illustrated, and but not limited to this, can also be suitable for using certainly
The heat exchanger for being aspirated through flat shape has carried out the tempering air of heat exchange, and from upper and lower blow-off outlet along centrifugal direction to room
The air-conditioning etc. of the mode of interior blowout.Also, turbofan 7 be readily applicable in itself the equipment other than air-conditioning be do not say and
Analogy.
Symbol description
1 air-conditioning, 7- turbofan (pressure fan), 8- heat exchanger, 10- wheel hub, 11- shield, 12- blade, 13- leading edge are (preceding
Edge line), 13A- concavity, 13B- convex, 14- rear (rear line), 14A- concavity, 15- suction surface, 16- pressure surface, 17- combination
Portion (hub side engaging portion), 17A, 17B- flexure plane, the engaging portion 18- (shroud engaging portion), 18A, 18B- flexure plane.
Claims (11)
1. a kind of turbofan, which is characterized in that have:
Wheel hub links with motor drive shaft and is driven in rotation；
Cyclic annular shield configures in opposite directions with the wheel hub, and forms air suction inlet；And
More blades, both ends are incorporated between the wheel hub and the shield, and the leading edge of inner circumferential side is relative to peripheral side
Rear be configured at direction of rotation side,
About the more blades, in the rear, the center portion in the span direction of the blade is in the span direction
The rear is set relative to the engaging portion of the wheel hub and the shield to anti-airflow direction in the range of 25%~75%
It is in a concave shape, concavity amount from the rear of the blade to anti-airflow direction (with-indicate) set relative to outer diameter fan D
At -0.0142D~-0.0153D range,
About the engaging portion of the blade and the wheel hub, the smooth flexure plane of opposite direction along direction of rotation or direction of rotation
It is formed throughout entire airflow direction.
2. turbofan according to claim 1, which is characterized in that
The leading edge of the blade is set as concavity to airflow direction relative to the engaging portion with the wheel hub and the shield
Or convex is set as to anti-airflow direction.
3. turbofan according to claim 2, which is characterized in that
Concavity amount from the leading edge of the blade to airflow direction (with+indicate) be set as relative to outer diameter fan D
The range of 0.0091D~0.0153D, to anti-airflow direction convex amount (with-indicate) be set as relative to outer diameter fan D-
0.0438D。
4. turbofan according to claim 2 or 3, which is characterized in that
About the leading edge of the blade, the center portion in the span direction of the blade the span direction 25%~
Concavity is set as to airflow direction in this way in the range of 75% or is set as convex to anti-airflow direction.
5. turbofan according to claim 1, which is characterized in that
The engaging portion of the blade and the wheel hub is set as the flexure plane smooth along the opposite direction of direction of rotation, the blade with
The engaging portion of the shield is set as the flexure plane smooth along direction of rotation.
6. turbofan according to claim 5, which is characterized in that
Opposite direction from the engaging portion of the blade and the wheel hub to direction of rotation flexure plane angle (with+indicate) phase
The range of the θ of 0.0563 θ~0.0972 is set as 1 pitch angles θ of the blade, with the engaging portion of the shield to rotation
The flexure plane in direction angle (with-indicate) relative to the blade 1 pitch angles θ be set as -0.0154 θ~-
The range of 0.0972 θ.
7. turbofan according to claim 2 or 3, which is characterized in that
The engaging portion of the blade and the wheel hub is set as the flexure plane smooth along direction of rotation, the blade and the shield
Engaging portion is set as the flexure plane smooth along the opposite direction of direction of rotation.
8. turbofan according to claim 7, which is characterized in that
Flexure plane from the engaging portion of the blade and the wheel hub to direction of rotation angle (with-indicate) relative to the leaf
1 pitch angles θ of piece is set as -0.0768 θ, with opposite direction from the engaging portion of the shield to direction of rotation flexure plane
Angle (with+indicate) 0.0031 θ is set as relative to 1 pitch angles θ of the blade.
9. turbofan according to claim 2 or 3, which is characterized in that
The engaging portion of the blade and the wheel hub is set as the flexure plane smooth along direction of rotation, the blade and the shield
Engaging portion is set as the flexure plane smooth along direction of rotation.
10. turbofan according to claim 9, which is characterized in that
Flexure plane from the engaging portion of the blade and the wheel hub to direction of rotation angle (with-indicate) relative to the leaf
1 pitch angles θ of piece is set as -0.0154 θ, with flexure plane from the engaging portion of the shield to direction of rotation angle (with-come
Indicate) -0.0461 θ is set as relative to 1 pitch angles θ of the blade.
11. a kind of air-conditioning, which is characterized in that have:
Pressure fan sucks room air and blows out；And
Heat exchanger, the either side being configured in the suction side or blowout side of the pressure fan, and the room air is carried out
Cooling or heating,
The pressure fan is set as turbofan described in any one of claims 1 to 3.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2015196839A JP6642913B2 (en) | 2015-10-02 | 2015-10-02 | Turbo fan and air conditioner using it |
| JP2015-196839 | 2015-10-02 | ||
| PCT/JP2016/076156 WO2017056874A1 (en) | 2015-10-02 | 2016-09-06 | Turbofan and air conditioner in which same is used |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107850081A CN107850081A (en) | 2018-03-27 |
| CN107850081B true CN107850081B (en) | 2019-10-01 |
Family
ID=58423422
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680042586.5A Active CN107850081B (en) | 2015-10-02 | 2016-09-06 | Turbofan and the air-conditioning for having used the turbofan |
Country Status (4)
| Country | Link |
|---|---|
| EP (1) | EP3315786A4 (en) |
| JP (1) | JP6642913B2 (en) |
| CN (1) | CN107850081B (en) |
| WO (1) | WO2017056874A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE112020007795T5 (en) | 2020-11-25 | 2023-09-28 | Mitsubishi Electric Corporation | TURBO FAN AND AIR CONDITIONING |
Citations (7)
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|---|---|---|---|---|
| JP2008144667A (en) * | 2006-12-11 | 2008-06-26 | Daikin Ind Ltd | Impeller for blower |
| WO2009128299A1 (en) * | 2008-04-18 | 2009-10-22 | 三菱電機株式会社 | Turbofan and air conditioner |
| EP2213882A1 (en) * | 2007-11-26 | 2010-08-04 | Daikin Industries, Ltd. | Centrifugal fan |
| JP2011226448A (en) * | 2010-04-23 | 2011-11-10 | Toshiba Carrier Corp | Centrifugal fan and air conditioner |
| JP2013096378A (en) * | 2011-11-04 | 2013-05-20 | Daikin Industries Ltd | Centrifugal air blower |
| JP2013124575A (en) * | 2011-12-14 | 2013-06-24 | Mitsubishi Electric Corp | Turbofan and air conditioner |
| WO2014061642A1 (en) * | 2012-10-16 | 2014-04-24 | 三菱電機株式会社 | Turbo fan and air conditioner |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1058200B (en) * | 1952-02-27 | 1959-05-27 | Bruno Eck Dr Ing | Sheet metal impeller for radial fan and meridian accelerated axial fan |
| JP2009127541A (en) * | 2007-11-26 | 2009-06-11 | Daikin Ind Ltd | Centrifugal fan |
| JP4994421B2 (en) * | 2009-05-08 | 2012-08-08 | 三菱電機株式会社 | Centrifugal fan and air conditioner |
-
2015
- 2015-10-02 JP JP2015196839A patent/JP6642913B2/en active Active
-
2016
- 2016-09-06 WO PCT/JP2016/076156 patent/WO2017056874A1/en active Application Filing
- 2016-09-06 CN CN201680042586.5A patent/CN107850081B/en active Active
- 2016-09-06 EP EP16851050.1A patent/EP3315786A4/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008144667A (en) * | 2006-12-11 | 2008-06-26 | Daikin Ind Ltd | Impeller for blower |
| EP2213882A1 (en) * | 2007-11-26 | 2010-08-04 | Daikin Industries, Ltd. | Centrifugal fan |
| WO2009128299A1 (en) * | 2008-04-18 | 2009-10-22 | 三菱電機株式会社 | Turbofan and air conditioner |
| JP2011226448A (en) * | 2010-04-23 | 2011-11-10 | Toshiba Carrier Corp | Centrifugal fan and air conditioner |
| JP2013096378A (en) * | 2011-11-04 | 2013-05-20 | Daikin Industries Ltd | Centrifugal air blower |
| JP2013124575A (en) * | 2011-12-14 | 2013-06-24 | Mitsubishi Electric Corp | Turbofan and air conditioner |
| WO2014061642A1 (en) * | 2012-10-16 | 2014-04-24 | 三菱電機株式会社 | Turbo fan and air conditioner |
Also Published As
| Publication number | Publication date |
|---|---|
| EP3315786A1 (en) | 2018-05-02 |
| WO2017056874A1 (en) | 2017-04-06 |
| CN107850081A (en) | 2018-03-27 |
| EP3315786A4 (en) | 2018-07-04 |
| JP6642913B2 (en) | 2020-02-12 |
| JP2017067056A (en) | 2017-04-06 |
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