CN107850081A

CN107850081A - Turbofan and the air-conditioning for having used the turbofan

Info

Publication number: CN107850081A
Application number: CN201680042586.5A
Authority: CN
Inventors: 江口刚; 松本创郎; 松本创一郎; 石塚浩史
Original assignee: Mitsubishi Heavy Industries Air Conditioning and Refrigeration Systems Corp
Current assignee: Mitsubishi Heavy Industries Ltd; Mitsubishi Heavy Industries Air Conditioning and Refrigeration Systems Corp
Priority date: 2015-10-02
Filing date: 2016-09-06
Publication date: 2018-03-27
Anticipated expiration: 2036-09-06
Also published as: CN107850081B; JP2017067056A; EP3315786A4; EP3315786A1; WO2017056874A1; JP6642913B2

Abstract

The present invention provides a kind of turbofan, it possesses the wheel hub (10) for linking and being driven in rotation with drive shaft, configured in opposite directions with wheel hub (10) and form the ring-type shield (11) of air suction inlet, and both ends are incorporated into the leading edge (13) of between wheel hub (10) and shield (11) and inner circumferential side and the more blades (12) of direction of rotation side are configured at relative to the trailing edge (14) of outer circumferential side, wherein, on more blades (12), trailing edge (14) is relative to the joint portion (17) with wheel hub (10) and shield (11), (18) it is set as concavity (14A) to anti-airflow direction.

Description

Turbofan and the air-conditioning for having used the turbofan

Technical field

The present invention relates to a kind of turbine wind that will change direction to radial direction from the air that shroud sucks vertically and blow out Fan and used the air-conditioning of the turbofan.

Background technology

Turbofan is by the wheel hub by rotation drivings such as motors, the shield configured in opposite directions with the wheel hub and is configured at wheel hub More blades between shield are formed.On the blade of the turbofan, between wheel hub and shield, the end of inner circumferential side is Leading edge is configured at more more more by the situation of direction of rotation side than the end i.e. trailing edge of outer circumferential side, and is shaped to wing section shape Situation is more, but because by being limited on being molded, its section shape be usually vertically identical two-dimensional shapes (for example, ginseng Examine patent document 1 etc.).But nowadays, manufacture method is gradually unrestricted, it was also proposed that has blade being set as three-dimensional shaped vertically Shape is set as the kinds of schemes such as the turbofan of hollow shape (for example, referenced patent document 2-4 etc.).

On the other hand, turn to target with low noise and efficiently and pay attention to the turbofan of performance, for example, such as patent document Shown in 5-7, proposition has to suppress caused U-vortex in the joint portion of wheel hub and blade, and is set as the wheel of blade The structure that hub side leading edge is nearby bent to the opposite direction of 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 for blade to rotation side To opposite direction bending, and the turbofan connected via the arc surface of the bending part and shield, or the wheel by 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 hinder marginal part of blade Turbofan of stream etc..

That is, when for turbofan when, due to the air flow sucked vertically is radially changed into direction, therefore from suction inlet The air stream of outer edge side suction can not bend completely because of inertia force, and easily internally turn into the fluid of deviation hub side, connecing The position blade of nearly suction inlet can not effectively play function, so as to cause efficiency to decline, and be produced in blowout side by air-flow Deviation caused by high speed jet stream, or adverse current is produced near suction inlet, so as to which noise easily becomes big.Also, work as turbine When fan is applied to air-conditioning, is sucking air from the quadrilateral shape path that have passed through grid and filter and blowing out side by quadrangle Worked under the nonaxisymmetrical pressure field that the heat exchanger of shape is surrounded, therefore throughout the span direction (axial direction) of whole fan, it is difficult To realize identical fluid, as described above, propose to have the various schemes for low noise and efficiently turning to target.

Conventional art document

Patent document

Patent document 1：Japanese Unexamined Patent Publication 2002-235695 publications

Patent document 2：Japanese Unexamined Patent Publication 2007-170331 publications

Patent document 3：Japanese Unexamined Patent Publication 2007-170771 publications

Patent document 4：Japanese Unexamined Patent Publication 2010-216486 publications

Patent document 5：Japanese Unexamined Patent Publication 2009-127541 publications

Patent document 6：International Publication No. 2009/069606

Patent document 7：International Publication No. 2010/128618

The content of the invention

The invention technical task to be solved

In foregoing turbofan and the air-conditioning of the turbofan is used, when by the driving force of turbofan being that fan is defeated When entering power and being set as evaluating, room for improvement still be present in turbofan.That is, it is eternal to reduce fan input power Problem, consider from the viewpoint, fluid analysis has been carried out to turbofan by finite volume method, its result specify that current In turbofan, in the suction surface of the outer circumferential side (rear side) of blade, exist and easily peeled off along the air stream of blade from aerofoil Trend, on the other hand, in the pressure surface side of blade, produce high static pressure region, (drive produced so as to slow down along the air stream of blade The loss of power), fan efficiency declines.

The present invention is to complete in light of this situation, and its object is to provide a kind of outer circumferential side by suppressing blade The stripping of air stream in the suction surface of (rear side), and suppress the deceleration of the air stream in the pressure surface side of blade, can Improve 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 above-mentioned problem, 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, it is characterised in that possesses：Wheel hub, it drives with motor Axle links and is driven in rotation；Ring-type shield, it is configured 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 trailing edge of outer circumferential side Turn direction side, on the more blades, the trailing edge relative to the joint portion of the wheel hub and the shield to anti-air Stream direction is set as concavity.

According to the manner, the trailing edge of more blades (also referred to as trailing edge line) is relative to the joint portion with wheel hub and shield to anti- Airflow direction is set as concavity, therefore with the trailing edge line of blade is set as into turbine linear and that convex is set as to airflow direction Fan is compared, and can be improved the stripping of the air stream in the negative pressure surface side of blade and can be suppressed the disorder of air stream, and lead to Caused high static pressure region in the malleation surface side for reducing blade is crossed, suppresses the deceleration (loss of driving force) of air stream and improves Fan efficiency, so as to reduce the driving force of fan (fan input power).That is, the reason is that by by 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 diminishes, when with same rotational speed During rotary fan, it can reduce and be risen by the pressure of the air stream of fan, thus, in suction surface especially in the easy of shroud The position of stripping, the pressure (static pressure) near trailing edge is reduced, therefore becomes easily to flow as air stream, so as to press down System is peeled off, and on the other hand, in pressure surface, the influence by the air stream deviation hub side of fan is notable, the pressure of blade surface Power also shows the distribution steeply risen towards hub side, but by the way that trailing edge line is set as into concavity, it is attached can to reduce trailing edge Near pressure (static pressure), and the static pressure in pressure surface can be reduced, fan efficiency is improved, so as to reduce fan input power.Cause This, can realize the further efficient, low noise of turbofan.

Also, in above-mentioned turbofan, the trailing edge on the blade, the span side of the blade can be set as To middle body 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 manner, the middle body of the trailing edge 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 does not interfere with blade and wheel hub and function, the performance of the joint portion of shield, and can incite somebody to action Blade is combined with wheel hub and shield.Therefore, air stream will not be upset in the hub side joint portion of blade and shroud joint portion, So as to realize low noise, high efficiency.

Moreover, in above-mentioned any turbofan, the trailing edge of the blade can be set as to anti-airflow direction Concavity amount (with-represent) be set as -0.0142D~-0.0153D scope relative to outer diameter fan D.

According to the manner, concavity amount from the trailing edge line of blade to anti-airflow direction (with-represent) relative to fan outside Footpath D is set as -0.0142D~-0.0153D scope, therefore can be the reduction of fan input power by the driving force of turbofan For preferred scope.Therefore, it is possible to by turbofan is efficient, low noise.

Moreover, in above-mentioned any turbofan, can be set as the leading edge of the blade relative to the wheel The joint 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 manner, the leading edge (also referred to as costa) of blade is relative to the joint portion with wheel hub and shield to air stream Direction is set as concavity or is set as convex to anti-airflow direction, thus by by costa to airflow direction with concavity displacement, And sometimes, small disorder occurs in air stream in the suction surface of blade, but the high static pressure region that can be reduced in malleation surface side And suppress the deceleration of air stream, on the other hand, by by costa to anti-airflow direction with convex displacement, and pressure surface sometimes High static pressure region in side somewhat becomes big and air stream deceleration inhibition and somewhat declined, but can suppress the sky in suction surface Air-flow disorder and suppress peel off.That is, by the way that the costa of blade is set as into concavity, the air stream side of blade to airflow direction Shortened to length, the friction loss of air stream and blade surface is reduced, so as to reduce fan input power.It is but if recessed Shape is excessively recessed, then is excessively shortened relative to the length of blade of the airflow direction of the distance between adjacent blade, and makes blade It can deteriorate.Also, by the way that the costa of blade is set as into 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 actual blade, therefore by will be flowed into from blade upstream side Fluid stable guide to downstream, suppress the peak value of the static pressure on blade surface and make fluid be difficult to peel off, so as to Fan input power is reduced, and fan noise can be reduced.Therefore, fan input also can be fully reduced in this case Power, the high efficiency and low noise of turbofan can be realized.

Moreover, in above-mentioned turbofan, the leading edge of the blade can be set as to the concavity amount of airflow direction (with+represent) 0.0091D~0.0153D scope is set as relative to outer diameter fan D, to the convex amount of anti-airflow direction (with-represent) relative to outer diameter fan D it is set as -0.0438D.

According to the manner, concavity amount from costa to airflow direction (with+represent) be set as relative to outer diameter fan D 0.0091D~0.0153D scope, to anti-airflow direction convex amount (with-represent) be set to relative to outer diameter fan D- 0.0438D, therefore can be that fan input power is reduced to preferred scope by the driving force of turbofan, thereby, it is possible to by whirlpool Take turns fan high efficiency, low noise.

Moreover, in above-mentioned any turbofan, the leading edge on the blade can be set as, the blade The middle body 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 manner, the middle body 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 does not interfere with blade and wheel hub and the knot of shield Function, the performance in conjunction portion, and blade can be combined with wheel hub and shield.Therefore, in the hub side joint portion of blade and shield Air stream will not be upset in the joint portion of side and can realize low noise, high efficiency.

Moreover, it can be set in above-mentioned any turbofan：The joint portion of the blade and the wheel hub is set as edge The joint 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 manner, the joint portion of blade and wheel hub is set as the smooth flexure plane of opposite direction along direction of rotation, leaf The joint portion of piece and shield is set as along the smooth flexure plane in direction of rotation, therefore by the way that the joint portion of blade and wheel hub is set as into edge The smooth flexure plane of the opposite direction of direction of rotation, joint portion is set as it is left-right asymmetry, so as to suppress in joint portion The stagnation of air stream, on the other hand, by the way that the joint portion of blade and shield is set as along the smooth flexure plane in direction of rotation, with the wing Power suppresses the stripping of the fluid in negative pressure surface side, so as to make air stream smooth.Therefore, Blade Properties are improved, further drop Low fan input power, so as to realize high efficiency, and suppress the disorder of air stream, so as to realize low noise.

Moreover, in above-mentioned turbofan, can be set to：The joint portion of the blade and the wheel hub is to direction of rotation The flexure plane of opposite direction angle (with+represent) relative to 1 pitch angles θ of the blade be set as 0.0563 θ~ 0.0972 θ scope, with angle from the joint portion of the shield to the flexure plane of direction of rotation (with-represent) relative to described 1 pitch angles θ of blade is set as the θ of -0.0154 θ~-0.0972 scope.

According to the manner, angle from the joint portion of blade and wheel hub to the flexure plane of the opposite direction of direction of rotation (with+come Represent) θ of 0.0563 θ~0.0972 scope is set as relative to 1 pitch angles θ of blade, with the joint portion of shield to rotation The flexure plane in direction angle (with-represent) be set as the θ's of -0.0154 θ~-0.0972 relative to 1 pitch angles θ of blade Scope, therefore the stagnation of the air stream in hub side joint portion can be suppressed, and the sky in negative pressure surface side is suppressed with wing power The stripping of air-flow, so as to further improve Blade Properties.Therefore, it is fan input power drop by the driving force of turbofan Low is preferred scope, so as to by turbofan is efficient, low noise.

Moreover, in above-mentioned any turbofan, can be set to：The joint portion of the blade and the wheel hub is set as edge The joint 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 manner, the joint portion of blade and wheel hub is set as along the smooth flexure plane in direction of rotation, blade and shield Joint portion is set as the smooth flexure plane of opposite direction along direction of rotation, therefore by the way that the joint portion of blade and wheel hub is set as into edge The smooth flexure plane of the opposite direction of direction of rotation, joint portion is set as it is left-right asymmetry, so as to suppress in joint portion The stagnation of air stream.Also, by the way that the joint portion of blade and shield is set as, along the smooth flexure plane in direction of rotation, to make shield attached Air stream near negative pressure surface side is smooth, so as to suppress to peel off.Therefore, Blade Properties are improved, further reduce fan Input power, so as to realize high efficiency, and suppress the disorder of air stream, so as to realize low noise.

Moreover, in above-mentioned turbofan, can be set to：The joint portion of the blade and the wheel hub is to direction of rotation Flexure plane angle (with-represent) relative to 1 pitch angles θ of the blade be set as -0.0768 θ, with the shield Angle from joint portion to the flexure plane of the opposite direction of direction of rotation (with+represent) relative to 1 pitch angle of the blade Degree θ is set as 0.0031 θ.

According to the manner, angle from the joint portion of blade and the wheel hub to the flexure plane of direction of rotation (with-represent) - 0.0768 θ is set as relative to 1 pitch angles θ of the blade, the phase negative side with the joint portion of the shield to direction of rotation To flexure plane angle (with+represent) relative to 1 pitch angles θ of the blade be set as 0.0031 θ, therefore can press down The stagnation of air stream in hub side joint portion processed, and suppress the stripping of the air stream in the negative pressure surface side near shield, from And it can further improve Blade Properties.Therefore, it is that fan input power is reduced to preferred scope by the driving force of turbofan, So as to by turbofan is efficient, low noise.

Also, in above-mentioned any turbofan, it can be set to：The joint portion of the blade and the wheel hub is set as edge The smooth flexure plane in direction of rotation, the joint portion of the blade and the shield are set as along the smooth flexure plane in direction of rotation.

According to the manner, the joint portion of blade and wheel hub is set as along the smooth flexure plane in direction of rotation, blade and shield Joint portion is set as along the smooth flexure plane in direction of rotation, therefore by the way that the joint portion of blade and wheel hub is set as along direction of rotation The smooth flexure plane of opposite direction, joint portion is set as it is left-right asymmetry, so as to suppress stopping for the air stream in joint portion It is stagnant, on the other hand, by the way that the joint portion of blade and shield is set as along the smooth flexure plane in direction of rotation, suppress negative with wing power The stripping of fluid in pressure surface side, so as to make air stream smooth.Therefore, Blade Properties are improved, it is defeated further to reduce fan Enter power, so as to realize high efficiency, and suppress the disorder of air stream, so as to realize low noise.

Moreover, in above-mentioned turbofan, can be set to：The joint portion of the blade and the wheel hub is to direction of rotation Flexure plane angle (with-represent) relative to 1 pitch angles θ of the blade be set as -0.0154 θ, with the shield Angle from joint portion to the flexure plane of direction of rotation (with-represent) be set as relative to 1 pitch angles θ of the blade- 0.0461θ。

According to the manner, angle from the joint portion of blade and wheel hub to the flexure plane of direction of rotation (with-represent) it is relative Be set as -0.0154 θ in 1 pitch angles θ of blade, with angle from the joint portion of shield to the flexure plane of direction of rotation (with-come Represent) -0.0461 θ is set as relative to 1 pitch angles θ of blade, therefore the air stream in hub side joint portion can be suppressed Stagnation, and suppress with wing power the stripping of the air stream in negative pressure surface side, so as to further improve Blade Properties.Cause This, is that fan input power is reduced to preferred scope by the driving force of turbofan, so as to which turbofan is efficient, low Noise.

Moreover, the 2nd aspect of the present invention provides a kind of air-conditioning, it is characterised in that possesses：Pressure fan, it sucks Interior Space Gas and blow out；And heat exchanger, it is configured at the either side in the suction side of the pressure fan or blowout side, and to the Interior Space Gas is cooled down or heated, and the pressure fan is set as above-mentioned any turbofan.

According to the manner, suction room air 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 the driving force for reducing turbofan is fan input power, from And the high efficiency of turbofan, low noise can be realized.Therefore, it is possible to by the further high performance of air-conditioning and low noise.

Invention effect

According to the turbofan of the present invention, the stripping of the air stream in the negative pressure surface side of blade can be improved, and can press down The disorder of air stream processed, and caused high static pressure region in the malleation surface side of blade is reduced, and suppress the deceleration of air stream (loss of driving force), thus, it is possible to improve fan efficiency, the driving force (fan input power) of fan, therefore energy can be reduced Enough realize the further efficient, low noise of turbofan.

According to the air-conditioning of the present invention, the driving force i.e. fan input power of turbofan can be reduced, and whirlpool can be realized High efficiency, the low noise of fan are taken turns, therefore air-conditioning can be reached to higher performance and low noise.

Brief description of the drawings

Fig. 1 is the exploded perspective view of the air-conditioning involved by one embodiment of the present invention.

Fig. 2 is the fan-shaped (A) for the turbofan for representing to be applicable in foregoing 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 foregoing 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 foregoing each turbofan.

Fig. 5 is the comparison figure of the static pressure isopleth (A) to (E) on the blade surface of foregoing each turbofan.

Fig. 6 is the displacement shape relative to the original shape (A) of the blade inlet edge of the design variable as foregoing 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 of the design variable as foregoing each turbofan The comparison figure of shape (B), (C).

Fig. 8 is the original shape relative to the blade wheel hub lateral bend shape of the design variable as foregoing each turbofan (A) displacement shape (B), the comparison figure of (C).

Fig. 9 is the original shape relative to the blade shroud lateral bending curved shape as the design variable for representing foregoing each turbofan The displacement shape (B) of shape (A), the comparison figure of (C).

Figure 10 is the blade 2 integrally rotated using the blade for the design variable for making foregoing each turbofan around rotating shaft center The coincidence pattern of piece part.

Figure 11 is 2 parts for the displacement for representing the leading edge and trailing edge for being used as the blade of the design variable of foregoing each turbofan Coincidence pattern.

Figure 12 is the leading edge of blade and the displacement state of trailing edge of design variable of the explanation as foregoing each turbofan Illustrate figure.

Figure 13 is the schematic diagram for illustrating the wing power of foregoing each turbofan.

Figure 14 is the table for representing design variable (A) and object function (B) used in the analysis of foregoing each turbofan Lattice.

Figure 15 is the form for representing the design variable value in the analysis result based on foregoing finite volume method.

Figure 16 is to represent that object function D'(corresponds to the ratio between air quantity power and original value) comparative result bar chart.

Figure 17 is the chart for the dependency relation for representing object function D' and design variable (1).

Figure 18 is the chart for the dependency relation for representing object function D' and design variable (2).

Figure 19 is the chart for the dependency relation for representing object function D' and design variable (3).

Figure 20 is the chart for the dependency relation for representing object function D' and design variable (4).

Embodiment

Hereinafter, one embodiment of the present invention is illustrated using Fig. 1 to Figure 20.

Figure 1 illustrates the exploded perspective view of the air-conditioning involved by one embodiment of the present invention.

Air-conditioning 1 involved by present embodiment is set as ceiling embedded type air conditioner 1, but the present invention is not limited to the smallpox Plate embedded type air conditioner 1, it can also be applied to the air-conditioning 1 of other patterns certainly.

The ceiling embedded type air conditioner 1 possesses the unit for the substantially quadrilateral shape that ceiling is arranged at by suspensions such as bolts Main body 2, it is arranged at below the unit main body 2 and possesses the quadrilateral shape of indoor air sucting inlet 4 and tempering air blow-off outlet 5 Ceiling panel 3, the loudspeaker to be configured at the indoor air sucting inlet 4 of ceiling panel 3 in a manner of opposite in unit main body 2 Mouth 6, top plate to be fixedly installed on unit main body 2 in a manner of opposite with horn mouth 6 turbofan (pressure fan) 7 and with The mode of encirclement turbofan (pressure fan) 7 is arranged at heat exchanger 8 of quadrilateral shape in unit main body 2 etc..

Turbofan 7 is to possess the motor 9 for the top plate for being fixedly installed on unit main body 2, combined with the rotary shaft 9A of motor 9 And the ring-type shield (side plate) 11 that is configured in opposite directions by the wheel hub (mainboard) 10 of the rotation driving of motor 9, with wheel hub (mainboard) 10 and The more blades 12 arranged in a manner of both ends are combined with wheel hub (mainboard) 10 and shield (side plate) 11 respectively without shell structure Fan.On the more blades 12 of the turbofan 7, leading edge (the otherwise referred to as costa of inner circumferential side.) 13 with relative to Trailing edge (the otherwise referred to as trailing edge line of outer circumferential side.) 14 configured positioned at the modes of direction of rotation N sides.

As shown in Fig. 2 (A), the turbofan 7 of present embodiment is set in a manner of described later to the shape of blade 12 Meter, thus, the limiting streamline (fluid that blade surface is visualized with wire) as shown in Fig. 2 (B), by the suction surface 15 of blade 12 Air stream in side is set as the clearly streamline of the drastically change less (not peeling off) at interval, and quiet as shown in Fig. 2 (C) Isogram is pressed, the static pressure in the side of pressure surface 16 of blade 12 is set as eliminating or reduces to the minimum high static pressure region and suppresses air The deceleration (loss) of stream, to reduce the driving force of turbofan 7 i.e. fan input power.

In the present embodiment, in order to be fan input power as a parameter to turbine by the driving force of turbofan 7 The performance of fan 7 is evaluated, and the state so that turbofan 7 is arranged in air-conditioning 1 is divided by finite volume method Analysis, and according to the shape of its analysis result setting blade 12.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 trailing edge 14 of (2) blade 12, the hub side of (3) blade 12 The bending (anglec of rotation) of joint portion 17 and the bending (anglec of rotation) of the shroud joint portion 18 of (4) blade 12 this 4 are used as design Variable, the Parameter analysis of 41 examples is evaluated.Moreover, with the shape (No.31) of the 1st in the Parameter analysis for base Plinth, optimum shape (No.59) is obtained.

Fig. 2 (A) and Fig. 3 (A) to Fig. 3 (E) is the fan (No.59) for showing optimum shape；Evaluated in Parameter analysis In 41 examples, 1 (No.31), 2 (No.32) and 3 (No.06) fan are evaluated as；Original-shape as metewand Fan (No.0)；And it is evaluated as the figure of the shape of the fan (No.14) of last position (41).In Fig. 2 (A) and Fig. 3 (A) extremely The detail shape of the fan shown in Fig. 3 (E) will be aftermentioned, but the fan of original-shape is set as following structure：As shown in Fig. 3 (D), The section of blade 12 is straight in being parallel to each other in identical two-dimensional shapes vertically, the costa 13 and trailing edge line 14 of blade 12 Line, the hub side joint portion 17 and shroud joint 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 minimum example No.14 fan-shaped is set as following structure：As shown in Fig. 3 (E), Relative to the original fan-shaped shown in Fig. 3 (D), the costa 13 of blade 12 is set as concavity 13A to airflow direction, will Trailing edge line 14 is set as convex 14B to airflow direction, and hub side joint portion 17 is set as into the opposite direction to direction of rotation The flexure plane 17A of bending, shroud joint portion 18 is set as to the flexure plane 18A of the opposite direction bending to direction of rotation.

Moreover, Fig. 4 (A) to (E) and Fig. 5 (A) show to compare into (E) with shown in Fig. 3 (A) to (E) The figure of the limiting streamline of each fan and static pressure isopleth corresponding to fan-shaped.

Here, shape, the structure of 4 foregoing design variable (1)~(4) are described in detail according to Fig. 6 to Fig. 9.

(1) displacement (amount of movement) of the leading edge 13 of blade 12 represents：As shown in fig. 6, relative to by the leading edge 13 of blade 12 The original-shape shown in linear Fig. 6 (A) is set as, as shown in Fig. 6 (B), costa 13 is set as relative to wheel hub 10 and shield Concavity 13A that the joint portion 17 and 18 of cover 11 is recessed to airflow direction (by amount of movement with+represent), 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-represent).

(2) displacement (amount of movement) of the trailing edge 14 of blade 12 represents：As shown in fig. 7, relative to by the trailing edge 14 of blade 12 The original-shape shown in linear Fig. 7 (A) is set as, as shown in Fig. 7 (B), trailing edge line 14 is set as relative to wheel hub 10 and shield Concavity 14A that the joint portion 17 and 18 of cover 11 is recessed to anti-airflow direction (by amount of movement with-represent), or such as Fig. 7 (C) institute Show, the convex 14B that is set as expanding to airflow direction (by amount of movement with+represent).

(3) bending (anglec of rotation) of the hub side joint portion 17 of blade 12 represents：As shown in figure 8, relative to by blade 12 Hub side joint portion 17 by with the side of wheel hub 10 in a manner of substantially rectangular with reference to Fig. 8 (A) shown in original-shape, such as Fig. 8 (B) shown in, the hub side joint portion 17 of blade 12 is set as the curved of opposite direction (counter clockwise direction) bending to direction of rotation During curved surface 17A relative to wheel hub 10 the anglec of rotation (by the anglec of rotation with+represent), or as shown in Fig. 8 (C), be set as to rotation side During the flexure plane 17B bent to (clockwise direction) relative to wheel hub 10 the anglec of rotation (by the anglec of rotation with-represent).

(4) bending (anglec of rotation) of the shroud joint portion 18 of blade 12 represents：As shown in figure 9, relative to by blade 12 Shroud joint portion 18 by with the side of shield 11 in a manner of substantially rectangular with reference to Fig. 9 (A) shown in original-shape, such as Fig. 9 (B) shown in, the shroud joint portion 18 of blade 12 is set as the curved of opposite direction (counter clockwise direction) bending to direction of rotation During curved surface 18A with the anglec of rotation of shield 11 (by the anglec of rotation with+represent), or as shown in Fig. 9 (C), be set as (suitable to direction of rotation Clockwise) bending flexure plane 18B when with the anglec of rotation of shield 11 (by the anglec of rotation with-represent).

In addition, the joint portion 17,18 on blade 12 and wheel hub 10 and shield 11, as shown in Figure 10, by blade entirety phase It is curved for rotary shaft 9A opposite directions (counter clockwise direction) or direction of rotation (clockwise direction) of the center O to direction of rotation Song, in case the angle between blade 12 and air stream changes.

Moreover, as shown in figure 11, the external diameter direction of blade 12 is set to+direction, in the sweep (ridge of blade (wing) 12 Line) and its extended line on, make blade 12 leading edge 13 and trailing edge 14 displacement (amount of movement) with concavely or convexly displacement.I.e., such as Shown in Figure 12, the leading edge 13 of blade 12 and the displacement of trailing edge 14 are in the side of leading edge 13 and this both sides of the side of trailing edge 14 in span direction It is set as in the range of substantially 25%~the 75% of the blade height of (axial rotary) along the mobile identical amount of sweep (crestal line) Concavely or convexly.Moreover, the structure connected respectively with smooth curve is set as in wheel hub 10 and shield 11.

Also, figure 13 illustrates the diagram of the wing power BF on turbofan 7.

The wing power BF of turbofan 7 acts on equivalent to the barometric gradient between acting on the multi-disc wing (blade 12), and for the wing It is the power of air stream in fluid, as shown in figure 13, by tilting the wing (blade 12), turns into wing power BF and act on aerofoil in straight The direction at angle.Wing power BF plays suppression suction surface by the way that air stream is pressed into wall (being the wall of shield 11 in Figure 13) The effect of the stripping of side.

Hereinafter, according to above-mentioned item, to the blade 12 to be set in a manner of the fan input power for reducing turbofan 7 Shape, structure is described in detail.

[optimum shape fan (example No.59)]

Fig. 2 (A) is the stereogram of the turbofan 7 for the blade 12 for possessing 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 figure 6 (B)) to airflow direction, and trailing edge line 14 to Anti- airflow direction is set as concavity 14A (with reference to figure 7 (B)) structure.

Also, the joint portion (hub side joint portion) 17 for being set as blade 12 and wheel hub 10 is set as the phase negative side to direction of rotation The flexure plane 17A (with reference to figure 8 (B)) bent to (counter clockwise direction), and (shroud is combined for the joint portion of blade 12 and shield 11 Portion) 18 be set as to direction of rotation (clockwise direction) bend flexure plane 18B (with reference to figure 9 (C)) structure.In addition, on this Hub side joint portion 17 and shroud joint portion 18, as shown in Figure 10, blade is overall to be bent relative to rotating shaft center O, in order to avoid Angle between blade 12 and air stream changes.

Moreover, foregoing costa 13 and trailing edge line 14 are set as following structure：As shown in Figure 11, Figure 12, passing through blade 12 Span direction (axial rotary) middle body in the range of the 25~75% of span direction size, in blade (wing) 12 Mobile equal amount on sweep (crestal line) and its extended line, costa 13 are set as concavity 13A to airflow direction, trailing edge line 14 to Anti- airflow direction is set as concavity 14A.

, will when the external diameter of turbofan 7 is set into 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 to θ [°] (with reference to figure 10), on previous designs variable (1) to (4), such as Figure 15 table institute Show, the displacement (amount of movement) of the leading edge (pull-LE) 13 of (1) blade 12 relative to airflow direction (with+represent) be set as phase When in 0.0153D concavity 13A, the displacement (amount of movement) of the trailing edge (pull-TE) 14 of (2) blade 12 is relative to anti-air stream side To (with-represent) it is set as concavity 14A equivalent to -0.0153D.

Also, (3) opposite direction (inverse time of the bending (anglec of rotation) of the hub side joint portion 17 of blade 12 to direction of rotation Pin direction, with+represent) it is set as 0.0972 θ flexure plane 17A, the bending (rotation of the shroud joint portion 18 of (4) blade 12 Angle) to direction of rotation (clockwise, with-represent) it is set as -0.0972 θ flexure plane 18B.

[example No.31 (1) fan-shaped]

The stereogram of the turbofan 7 for the blade shape for possessing example No.31 (1) is shown in Fig. 3 (A).

Identically with the blade 12 of optimum shape, the blade 12 is set as costa 13 and is set as concavity 13A to airflow direction (with reference to figure 6 (B)), and trailing edge line 14 is set as concavity 14A (with reference to figure 7 (B)) structure to anti-airflow direction.

Moreover, costa 13 and trailing edge line 14 are set as following structure：As shown in FIG. 11 and 12, by blade 12 across Middle body 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 trailing edge line 14 is to anti-sky Airflow direction is set as concavity 14A.

In the blade 12 of example No.31 (1), on previous designs variable (1) to (4), as shown in Figure 15 table, (1) displacement (amount of movement) of the leading edge (pull-LE) 13 of blade 12 relative to airflow direction (with+represent) be set as equivalent to 0.0153D concavity 13A, the displacement (amount of movement) of the trailing edge (pull-TE) 14 of (2) blade 12 is relative to anti-airflow direction (with-represent) it is set as concavity 14A equivalent to -0.0153D.

Also, (3) opposite direction (inverse time of the bending (anglec of rotation) of the hub side joint portion 17 of blade 12 to direction of rotation Pin direction, with+represent) it is set as 0.0563 θ flexure plane 17A, the bending (rotation of the shroud joint portion 18 of (4) blade 12 Angle) to direction of rotation (clockwise, with-represent) it is set as -0.0154 θ flexure plane 18B.

[example No.32 (2) fan-shaped]

The stereogram of the turbofan 7 for the blade shape for possessing example No.32 (2) is shown in Fig. 3 (B).

On the other hand, be set as blade 12 and wheel hub 10 joint portion (hub side joint portion) 17 be set as it is (suitable to direction of rotation Clockwise) bending flexure plane 17B (with reference to figure 8 (C)), and the joint portion (shroud joint portion) 18 of blade 12 and shield 11 It is set as the flexure plane 18A (with reference to figure 9 (B)) of structure from opposite direction (counter clockwise direction) bending to direction of rotation.In addition, close In the hub side joint portion 17 and shroud joint portion 18, as shown in Figure 10, blade is overall to be bent relative to rotating shaft center O, In order to avoid the angle between blade 12 and air stream changes.

In the blade 12 of example No.32 (2), on previous designs variable (1) to (4), as shown in Figure 15 table, (1) displacement (amount of movement) of the leading edge (pull-LE) 13 of blade 12 relative to airflow direction (with+represent) be set as equivalent to 0.0091D concavity 13A, the displacement (amount of movement) of the trailing edge (pull-TE) 14 of (2) blade 12 is relative to anti-airflow direction (with-represent) it is set as concavity 14A equivalent to -0.0142D.

Also, the bending (anglec of rotation) of the hub side joint portion 17 of blade 12 (3) to direction of rotation (clockwise, With-represent) be set as -0.0768 θ flexure plane 17B, the bending (anglec of rotation) of the shroud joint portion 18 of the blade 12 of (4) to The opposite direction (counterclockwise, with+represent) of direction of rotation is set as 0.0031 θ flexure plane 18A.

[example No.06 (3) fan-shaped]

The stereogram of the turbofan 7 for the blade shape for possessing 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 figure 6 (C)), and trailing edge line 14 to anti-airflow direction Concavity 14A (with reference to figure 7 (B)) structure is set as to anti-airflow direction.

On the other hand, be set as blade 12 and wheel hub 10 joint portion (hub side joint portion) 17 be set as it is (suitable to direction of rotation Clockwise) bending flexure plane 17B (with reference to figure 8 (C)), and the joint portion (shroud joint portion) 18 of blade 12 and shield 11 It is set as the flexure plane 18B (with reference to figure 9 (C)) of structure from opposite direction (counter clockwise direction) bending to direction of rotation.In addition, close In the hub side joint portion 17 and shroud joint portion 18, as shown in Figure 10, blade is overall 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 trailing edge line 14 are set as following structure, as shown in FIG. 11 and 12, by blade 12 across Middle body 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 trailing edge line 14 is to anti- Airflow direction is set as concavity 14A.

In the blade 12 of example No.06 (3), on previous designs variable (1) to (4), as shown in Figure 15 table, (1) displacement (amount of movement) of the leading edge (pull-LE) 13 of blade 12 to anti-airflow direction (with-represent) be set as equivalent to- 0.0438D convex 13B, the displacement (amount of movement) of the trailing edge (pull-TE) 14 of (2) blade 12 is relative to anti-airflow direction (with-represent) it is set as concavity 14A equivalent to -0.0153D.

Also, the bending (anglec of rotation) of the hub side joint portion 17 of blade 12 (3) to direction of rotation (clockwise, With-represent) be set as -0.0154 θ flexure plane 17B, the bending (anglec of rotation) of the shroud joint portion 18 of the blade 12 of (4) to Direction of rotation (clockwise, with-represent) is set as -0.0461 θ flexure plane 18B.

In addition, the original blade shape on example No.0, as shown in Figure 15 table, 4 design variables (1) to (4) It is set to 0.Also, on evaluating minimum (41) example No.14 blade shape, (1) is by the leading edge (pull- of blade 12 LE) 13 displacement (amount of movement) to airflow direction (with+represent) be set as concavity 13A equivalent to 0.0153D, and (2) will The displacement (amount of movement) of trailing edge (pull-TE) 14 relative to airflow direction (with+represent) be set as it is convex equivalent to 0.0438D Shape 14B, (3) by opposite direction from the bending (anglec of rotation) of the hub side joint portion 17 of blade 12 to direction of rotation (with+carry out table Show) be set as 0.0563 θ flexure plane 17A, and (4) by the bending (anglec of rotation) of shroud joint portion 18 to the opposite of direction of rotation Direction (with+represent) it is set as 0.0358 flexure plane 18A.

By structure described above, according to present embodiment, following action effect is played.

In foregoing turbofan 7 and air-conditioning 1, by the rotation of turbofan 7 and from the room air of ceiling panel 3 The room air that suction inlet 4 sucks is inhaled into vertically via horn mouth 6 from the opening portion of the side of shield 11 of turbofan 7.Inhale The air circulation entered to turbofan 7 is crossed after more blades 12 change direction to radial direction and is blown, and by surround whirlpool It is cooled during the heat exchanger 8 that arranges of mode of wheel fan 7 or heating, thus as temperature adjustment wind from ceiling panel 3 Four sides on set 4 temperature adjustment blow-off outlets 5 blow to the indoor temperature adjustment for interior.

When for turbofan 7 when, by the air flow sucked vertically, radially (centrifugal direction) changes direction, therefore especially The air stream that (side of shield 11) sucks near the outer rim of suction inlet turns into inclined because inertia force can not be bent completely inside fan To the fluid of the side of wheel hub 10, close to side, blade 12 can not effectively play function, and efficiency declines with shield 11, and Blow out side and produce the high speed jet stream as caused by the deviation of air-flow, or adverse current is produced in suction side, so as to which aerodynamic noise holds It is variable big.Also, when suitable for air-conditioning 1, air is inhaled into from the air channel of quadrilateral shape, in the heat exchanger 8 by quadrilateral shape Situation about being worked in the nonaxisymmetrical pressure field surrounded is more, it is difficult to realizes identical throughout the span direction of whole fan Fluid.

Therefore, the turbofan 7 involved by present embodiment is by 4 projects of foregoing (1) to (4) shown in Figure 14 (A) 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, object function D' definition is shown in Figure 14 (B).Also, in Figure 15 list, summarize Design variable value in analysis result based on finite volume method.

Only shown in the list of earlier figures 15：The fan of example No.59 optimum shape；The Parameter analysis of 41 examples High 1 (example No.31), 2 (example No.32) and 3 (example No.06) this 3 fans of middle evaluation；As metewand Original fan (example No.0)；And minimum 41 (the example No.14) of evaluation fan amounts to the result of 6 examples.

Moreover, in figure 16, on preceding aim function D', show to compare the bar chart of the value of foregoing 6 examples, In Figure 17 into Figure 20, show and represent object function D' and design variable (1), object function D' and design variable (2), target Function D' and design variable (3) and object function D' and the chart of the dependency relation of design variable (4).

It is clear that by these analysis results, the turbofan 7 of present embodiment is set as following structure：Such as Fig. 2 (A) or figure Shown in 3 (A) to Fig. 3 (C), the middle body of the trailing edge 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 the side of suction surface 15 of blade 12 can be set as The drastically change at limiting streamline (fluid that blade surface is visualized with wire) interval shown in Fig. 2 (B) or Fig. 4 (A) to Fig. 4 (C) Change the clearly streamline of less (not peeling off).

That is, example No.0 original-shape and evaluate example No.14 into last, such as Fig. 4 (D) and Fig. 4 (E) Shown limiting streamline, finds the disorderly position X of the air stream of the side of suction surface 15 of blade 12, peeling-off in air stream, but The example No.59 shown in Fig. 2 (A) or Fig. 3 (A) to Fig. 3 (C) optimum shape or evaluate example No.31 into 1~3, thing In example No.32 and example No.6, the position X in the limiting streamline of suction surface 15 without disorder, it is known that the stripping in suction surface 15 It is improved.

Also, static pressure (aerofoil pressure), but its are distributed in the pressure surface 16 of blade 12 by the rotation of turbofan 7 Static pressure is higher or high static pressure region is bigger, more slows down along the air stream of blade 12, represents because of its loss and fan efficiency decline. 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 example No.14 into last, such as Fig. 5 (D) and Fig. 5 (E) Shown, caused high static pressure region Y is occurred with larger region Y in the pressure surface 16 of blade 12, 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 into the example No.31, example No.32 and example of 1~3 Understand that high static pressure region Y does not occur in No.6, or as very small region Y, do not produce the deceleration of air stream, do not occur by subtracting Lost caused by fast and the situation of fan efficiency decline.

In this way, by the way that the trailing edge line 14 of blade 12 is set as into concavity 14A to anti-airflow direction, improve the negative pressure of blade 12 The stripping of air stream in the side of face 15, so as to suppress the disorder of air stream, and it is distributed by reducing in the side of pressure surface 16 High static pressure region Y, suppress the deceleration of air stream, so as to improve fan efficiency, as shown in Figure 16 and Figure 18, turbine can be reduced The driving force of fan 7 is fan input power.

The reason for this is that by the way that the trailing edge line 14 of blade 12 is set as into concavity 14A to anti-airflow direction, when being set as concavity The original shape of radius ratio in region diminish, and when rotating turbofan 7 with same rotational speed, can reduce by turbine wind The pressure of the air stream of fan 7 rises, thus, behind the position that suction surface 15 is especially easily peeled off in the side of shield 11, blade 12 Pressure (static pressure) near edge 14 is reduced, therefore becomes easily to flow as air stream, so as to suppress to peel off.

On the other hand, in pressure surface 16, the influence by air stream deviation wheel hub 10 side of turbofan 7 is notable, and And the pressure on the surface of blade 12 also shows the distribution that is steeply risen towards the side of wheel hub 10, but it is recessed by the way that trailing edge line 14 is set as Shape 14A, the pressure (static pressure) near the trailing edge 14 of blade 12 can be reduced, and the static pressure in pressure surface 16 can be reduced, therefore The fan efficiency of turbofan 7 can be improved, so as to reduce fan input power, therefore, it is possible to realize turbofan 7 Further low noise, high efficiency.

Also, it is because of the 25 of the middle body in span direction that trailing edge line 14 is set as into concavity 14A to anti-airflow direction ~75% scope is preferable, does not interfere with function, the performance of the joint portion 17,18 with 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 joint portion 17 and shroud joint portion 18 Stream, so as to realize low noise, high efficiency.

Moreover, when the external diameter of turbofan 7 is set into D, by by the trailing edge line 14 of blade 12 to anti-airflow direction Concavity amount (with-represent) be set as -0.0142D~-0.0153D scope, as shown in Figure 16 and Figure 18, can be by turbine wind The driving force of fan 7 is that fan input power is reduced to preferred scope.

On the other hand, in the turbofan 7 of present embodiment, on the costa 13 of blade 12, such as Fig. 2 (A) or Fig. 3 (A), shown in (B), by middle body in the range of the 25~75% of span direction (axial rotary) relative to wheel hub 10 and The joint 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, by by costa 13 to airflow direction with concavity 13A displacements, the leaf with the optimum shape shown in Fig. 2 Piece 12 is compared, and as shown in Fig. 4 (B), small disorder occurs in air stream in the side of suction surface 15 of blade 12 sometimes, but with such as High static pressure region that mode shown in Fig. 5 (B) is reduced in the side of pressure surface 16 and the deceleration of air stream can be suppressed, on the other hand, By by costa 13 to anti-airflow direction with convex 13B displacements, as shown in Fig. 5 (C), the height in the side of pressure surface 16 sometimes Static pressure field somewhat becomes big, and the deceleration inhibition of air stream somewhat reduces, but suppresses negative in a manner of as shown in Fig. 4 (C) The disorder of air stream in pressure surface 15 and can suppress to peel off.

Because by the way that the costa 13 of blade 12 is set as into concavity 13A, the air stream of blade 12 to airflow direction Direction length shortens, and air stream and the friction loss on the surface of 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 relative to the airflow direction of 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 into convex to anti-airflow direction 13B, usual air stream and the friction loss increase on the surface of blade 12, on the other hand, the airflow direction of actual blade 12 Length, therefore by guiding the fluid stable flowed into from blade upstream side to downstream, the surface of suppression blade 12 On static pressure peak value and make fluid be difficult to peel off, so as to reduce fan input power, and fan noise can be reduced.

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 high efficiency of turbofan 7 and low noise.

Also, in this case, as shown in Fig. 2 (A) or Fig. 3 (A) to Fig. 3 (C), also by the costa 13 of blade 12 Centre part is in the range of the 25~75% of span direction (axial rotary) relative to the joint portion 17 with wheel hub 10 and shield 11 And 18 be set as concavity 13A to airflow direction, or convex 13B is set as to anti-airflow direction, therefore do not interfered with and wheel hub 10 And function, the performance of the joint portion 17,18 of shield 11, and blade 12 can be combined with wheel hub 10 and shield 11.Therefore, taking turns Air stream will not be upset in hub side joint portion 17 and shroud joint portion 18, so as to realize low noise, high efficiency.

Also, in the costa 13 of foregoing blade 12, by the concavity 13A of airflow direction concavity amount (with+come Represent) 0.0091D~0.0153D scope is set as relative to outer diameter fan D, by the convex of the convex 13B of anti-airflow direction Shape amount (with-represent) -0.0438D is set as relative to outer diameter fan D, therefore as shown in Figure 16 and Figure 18, can by turbine wind The driving force of fan 7 is that fan input power is reduced to preferred scope.Thereby, it is possible to by the low noise of turbofan 7, high efficiency.

Moreover, as shown in Fig. 2 (A) and Fig. 3 (A), the turbofan 7 of present embodiment is set as the knot of blade 12 and wheel hub 10 Conjunction portion (hub side joint portion) 17 is set as the smooth flexure plane 17A of opposite direction along direction of rotation, and blade 12 and shield 11 Joint portion (shroud joint portion) 18 be set as structure along the smooth flexure plane 18B in direction of rotation.

In this way, the bending smooth by the way that the joint portion 17 of blade 12 and wheel hub 10 to be set as to opposite direction along direction of rotation Face 17A, the joint portion 17 with wheel hub 10 is set as it is left-right asymmetry, so as to suppress stopping for the air stream in the joint portion 17 It is stagnant, and by the way that the joint portion of blade 12 and shield 11 is set as along the smooth flexure plane 18B in direction of rotation, suppressed with wing power BF The stripping of fluid, so as to make air stream smooth.Meanwhile as shown in Fig. 2 (B) and Fig. 4 (A), the negative of blade 12 can be suppressed The disorder of air stream in the side of pressure surface 15, and as shown in Fig. 2 (C) and Fig. 5 (A), by the side of pressure surface 16 for reducing blade 12 In high static pressure region and the deceleration (loss of driving force) of air stream can be suppressed.

Therefore, the Blade Properties of turbofan 7 are improved, as shown in Figure 16, Figure 19 and Figure 20, turbofan 7 can be reduced Driving force be fan input power, so as to realize high efficiency, and suppress the disorder of air stream, so as to realize low noise Change.

Also, in the present embodiment, it is set as the joint portion (hub side joint portion) 17 of blade 12 and wheel hub 10 to rotation Turn the flexure plane 17A of the opposite direction in direction angle (with+represent) be set as relative to 1 pitch angles θ of blade 12 The θ of 0.0563 θ~0.0972 scope, and by the flexure plane with the joint portion of shield 11 (shroud joint portion) 18 to direction of rotation 18B angle (with-represent) be set as relative to 1 pitch angles θ of blade the θ of -0.0154 θ~-0.0972 scope knot Structure.

Therefore, it is possible to suppressing the stagnation of the air stream in the hub side joint portion 17 of blade 12, and suppressed with wing power The stripping of air stream in the side of suction surface 15, so as to further improve the performance of blade 12, thus, such as Figure 16, Figure 19 and Figure 20 It is shown, can be high by turbofan 7 also by being that fan input power is reduced to preferred scope by the driving force of turbofan 7 Effectization, low noise.

In addition, the present invention is not limited to the invention involved by aforementioned embodiments, in scope without departing from the spirit, Can suitably it be deformed.For example, in the foregoing embodiment, the day to being equipped with heat exchanger 8 in the blowout side of turbofan 7 The example being applicable in card embedded type air conditioner 1 is illustrated, but is not limited to this, can also be applied to employ 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 Air-conditioning of the mode of interior blowout etc..Also, the equipment that turbofan 7 is readily applicable in addition to air-conditioning in itself be do not say and Analogy.

Symbol description

1 air-conditioning, 7- turbofan (pressure fan), 8- heat exchangers, 10- wheel hubs, 11- shields, 12- blades, 13- leading edges are (preceding Edge line), 13A- concavities, 13B- convexs, 14- trailing edges (trailing edge line), 14A- concavities, 15- suction surfaces, 16- pressure surfaces, 17- combinations Portion (hub side joint portion), 17A, 17B- flexure plane, 18- joint portions (shroud joint portion), 18A, 18B- flexure plane.

Claims (according to the 19th article of modification of treaty)

1. a kind of turbofan (after correction), it is characterised in that possess：

Wheel hub, it links and is driven in rotation with motor drive shaft；

Ring-type shield, it is configured in opposite directions with the wheel hub, and forms air suction inlet；And

More blades, its both ends are incorporated between the wheel hub and the shield, and the leading edge of inner circumferential side is relative to outer circumferential side Trailing edge be configured at direction of rotation side,

On the more blades, the trailing edge relative to the joint portion of the wheel hub and the shield to anti-airflow direction It is set as concavity,

On the joint portion of the blade and the wheel hub, the smooth flexure plane of opposite direction along direction of rotation or direction of rotation Formed throughout whole airflow direction.

2. turbofan according to claim 1, it is characterised in that

On the trailing edge of the blade, the middle body in the span direction of the blade the span direction 25%~ Concavity is set as in the range of 75% to anti-airflow direction in this way.

3. turbofan according to claim 1 or 2, it is characterised in that

Concavity amount from the trailing edge of the blade to anti-airflow direction (with-represent) be set as relative to outer diameter fan D- 0.0142D~-0.0153D scope.

4. turbofan according to any one of claim 1 to 3, it is characterised in that

The leading edge of the blade is set as concavity relative to the joint portion with the wheel hub and the shield to airflow direction Or it is set as convex to anti-airflow direction.

5. turbofan according to claim 4, it is characterised in that

Concavity amount from the leading edge of the blade to airflow direction (with+represent) be set as relative to outer diameter fan D 0.0091D~0.0153D scope, to anti-airflow direction convex amount (with-represent) be set as relative to outer diameter fan D- 0.0438D。

6. the turbofan according to claim 4 or 5, it is characterised in that

On the leading edge of the blade, the middle body in the span direction of the blade the span direction 25%~ Concavity is set as in the range of 75% to airflow direction in this way or is set as convex to anti-airflow direction.

7. turbofan according to any one of claim 1 to 3, it is characterised in that

The joint portion of the blade and the wheel hub is set as the smooth flexure plane of opposite direction along direction of rotation, the blade with The joint portion of the shield is set as along the smooth flexure plane in direction of rotation.

8. turbofan according to claim 7, it is characterised in that

Angle from the joint portion of the blade and the wheel hub to the flexure plane of the opposite direction of direction of rotation (with+represent) phase The θ of 0.0563 θ~0.0972 scope is set as 1 pitch angles θ of the blade, with the joint portion of the shield to rotation The flexure plane in direction angle (with-represent) relative to 1 pitch angles θ of the blade be set as -0.0154 θ~- 0.0972 θ scope.

9. the turbofan according to any one of claim 4 to 6, it is characterised in that

The joint portion of the blade and the wheel hub is set as along the smooth flexure plane in direction of rotation, the blade and the shield Joint portion is set as the smooth flexure plane of opposite direction along direction of rotation.

10. turbofan according to claim 9, it is characterised in that

Angle from the joint portion of the blade and the wheel hub to the flexure plane of direction of rotation (with-represent) relative to the leaf 1 pitch angles θ of piece is set as -0.0768 θ, the flexure plane with the joint portion of the shield to the opposite direction of direction of rotation Angle (with+represent) relative to 1 pitch angles θ of the blade it is set as 0.0031 θ.

11. the turbofan according to any one of claim 4 to 6, it is characterised in that

The joint portion of the blade and the wheel hub is set as along the smooth flexure plane in direction of rotation, the blade and the shield Joint portion is set as along the smooth flexure plane in direction of rotation.

12. turbofan according to claim 11, it is characterised in that

Angle from the joint portion of the blade and the wheel hub to the flexure plane of direction of rotation (with-represent) relative to the leaf 1 pitch angles θ of piece is set as -0.0154 θ, with angle from the joint portion of the shield to the flexure plane of direction of rotation (with-come Represent) it is set as -0.0461 θ relative to 1 pitch angles θ of the blade.

13. a kind of air-conditioning, it is characterised in that possess：

Pressure fan, it sucks room air and blown out；And

Heat exchanger, it is configured at the either side in the suction side of the pressure fan or blowout side, and the room air is carried out Cooling or heating,

The pressure fan is set as the turbofan any one of claim 1 to 12.

Claims

1. a kind of turbofan, it is characterised in that possess：