EP0383238A2 - Wirbelstromgebläse und Verfahren zu dessen Herstellung - Google Patents

Wirbelstromgebläse und Verfahren zu dessen Herstellung Download PDF

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Publication number
EP0383238A2
EP0383238A2 EP90102729A EP90102729A EP0383238A2 EP 0383238 A2 EP0383238 A2 EP 0383238A2 EP 90102729 A EP90102729 A EP 90102729A EP 90102729 A EP90102729 A EP 90102729A EP 0383238 A2 EP0383238 A2 EP 0383238A2
Authority
EP
European Patent Office
Prior art keywords
impeller
blade
blades
annular passage
shroud
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP90102729A
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English (en)
French (fr)
Other versions
EP0383238A3 (de
EP0383238B1 (de
Inventor
Susumu Yamazaki
Eiichi Ito
Hiroshi Asabuki
Masayuki Fujio
Hajime Fujita
Kazuo Kobayashi
Kengo Hasegawa
Yukio Chihara
Hiromoto Ashihara
Takashi Watanabe
Kanzi Mizutani
Yuichi Nakatsuhama
Yukio Makuta
Kazuo Yanagiya
Tomoya Tamura
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hitachi Ltd
Original Assignee
Hitachi Ltd
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Publication date
Priority claimed from JP1031033A external-priority patent/JPH02215997A/ja
Application filed by Hitachi Ltd filed Critical Hitachi Ltd
Publication of EP0383238A2 publication Critical patent/EP0383238A2/de
Publication of EP0383238A3 publication Critical patent/EP0383238A3/de
Application granted granted Critical
Publication of EP0383238B1 publication Critical patent/EP0383238B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D23/00—Other rotary non-positive-displacement pumps
    • F04D23/008—Regenerative pumps
    • 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

Definitions

  • the present invention relates to a vortex flow blower used as an air source to be incorporated into a general industrial machine such as an apparatus for transporting pulverized materials, an absorber for paper or an aeration apparatus, and, more particularly, to the shape of impeller blades capable of significantly improving the aerodynamic performance of a vortex flow blower, the shape of a casing suitable for the shape of the blades and a manufacturing method therefor.
  • the vortex flow blower has usually been provided with blades formed radially in the impeller. Since the vortex flow blower exhibits an advantage in that high wind pressure can be obtained with reduced size, a variety of disclosures and studies have been made for the purpose of improving the above-described advantage.
  • R 2 must be a small value for the purpose of reducing the size of the vortex flow blower, the following problems arise: namely, the value of Ri/R 2 must be decreased when the desired flow rate is satisfied with a reduced size of the vortex flow blower since the flow rate significantly depends upon the value of R 2 2 (1-Ri/R 2 ). However, if the value of Ri/R 2 is reduced to 0.75 or less, the pressure coefficient becomes smaller as described above. Furthermore, since the outer radius R 2 has been reduced, peripheral speed U2 at the outer radius R 2 is also lowered, thereby causing the discharge pressure to be excessively lowered since the pressure characteristic is determined by the product of the pressure coefficient and the square of U2 . Therefore, R 2 must be a small value, and Ri/R 2 must be a small value and the pressure coefficient must be significantly increased in order to reduce the size of the vortex flow blower.
  • Vortex flow blowers designed to improve their aerodynamic performance are disclosed, for example, in Japanese Patent Unexamined Publication No. 50-5914 and Japanese Patent Unexamined Publication No. 61-155696, each of which is provided with an impeller formed in such a manner that only the axial inlet angle and the exit angle of its blade are inclined at a certain angle which is respectively smaller or larger than 90 degrees.
  • vortex flow blowers although their objects are unclear, are disclosed in Japanese Utility Model Examined Publication No. 55-48158 and Japanese Utility Model Unexamined Publication No. 56-85091, each of which is provided with an impeller formed in such a manner that both or one of the inlet angle and the exit angle in the circumferential direction of its blade are or is inclined at a certain angle which is different from 90 degrees.
  • an impeller is disclosed in Japanese Patent Unexamined Publication No. 51-57011, and according to this method the impeller is composed of two pieces divided in its axial direction in order to make a core unnecessary when forming the impeller from a casting, and the thus divided two pieces are coupled to each other afterwards.
  • the vortex flow blower Since the vortex flow blower exhibits an advantage in that it can serve as a clean air source with a reduced size, it has been widely used recently. Therefore, there arises a desire for the vortex flow blower which is capable of generating higher wind pressure and whose size is reduced with the discharge pressure maintained as it is.
  • the conventional technologies including the above-described technologies only one of the exit angle in the circumferential direction, the inlet angle and the axial angle of the blade is taken into consideration and the shape of the blade is not formed so as to be adapted to the three dimensional internal flow which takes place inherently in the vortex flow blower, so that turbulence of internal flow such as swirls and stagnations cannot be prevented. Therefore, the following problems take place: namely,
  • the impeller is manufactured die-casting or low pressure casting process, since there are problems of run or fluidity it is difficult to reduce thickness of the blade. Therefore, it is difficult to reduce the secondary moment of inertia of the impeller, thereby causing a necessity of starting torque when starting the impeller and, as a result, the size of the motor cannot be reduced.
  • the metal mold used when the impeller is manufactured by an integral molding process such as die-casting or chill-casting process is expensive, so that it is difficult to cheaply manufacture an impeller having different aerodynamic performance.
  • the present invention has been accomplished in-view of the foregoing, and a first object of the present invention is to provide a vortex flow blower exhibiting improved aerodynamic performance in comparison with conventional vortex flow blower.
  • a second object of the present invention is to provide a vortex flow blower whose noise is reduced.
  • a third object of the present invention is to provide a vortex flow blower whose aerodynamic performance is significantly improved and whose discharge pressure can be controlled to a set value.
  • a fourth object of the present invention is to provide a vortex blower whose size is reduced.
  • a fifth object of the present invention is to provide a method of efficiently and easily manufacturing an impeller even if it has a complicated shape.
  • a sixth object of the present invention is to provide a method of manufacturing an impeller having reduced secondary moment of inertia.
  • a seventh object of the present invention is to provide a method of cheaply manufacturing impellers having different aerodynamic characteristics by manufacturing only the blades of different shapes.
  • the first aspect of the present invention lies in that the shape of the blade is formed in a proper three dimensional shape such that at least the inner portion of the blade is adapted to the three dimensional internal flow.
  • the shape of the blade is formed by a surface smoothly curved so as to make at least ⁇ 1 , y; and ⁇ c smaller than 90 degrees and to meet the relationship of y; > ⁇ c or ⁇ 1 > ⁇ c. Further, it may be formed so as to make y 1 smaller than 90 degrees and to meet the relationship of -y i > ⁇ c .
  • the position of the blade at its front edge on a circle whose radius is R c is arranged to delay with respect to the direction of rotation of the impeller than that at its inner end.
  • the second aspect lies in that the shape of the blade of the impeller is three dimensionally formed such that the inner and the outer portions of the blade are adapted to the three dimensional internal flow, thereby projecting the front edge of the outer portion of the blade with respect to the direction of rotation of the impeller.
  • the third aspect lies in that the front edge of the outer portion of the blade is retracted with respect to the direction of rotation of the impeller and ⁇ o is made larger than 90 degrees.
  • the fourth aspect lies in that as mentioned before the shape of the blade of the impeller is three dimensionally formed and Ri R 2 is set to 0.75 or less and preferably to a range between 0.75 or less and 0.3 or more.
  • the fifth aspect lies in that the shape of the casing of the vortex flow blower is formed in such a manner that the shape of a partition wall thereof is formed so as to cause fluid to be introduced and discharged along the shape of the blade.
  • the method of manufacturing an impeller according to the present invention comprises the steps of independently manufacturing the shroud and the blades and coupling the thus independently manufactured shroud and the blades so as to form the impeller. Further, as occasion demands, a filler may be filled into the corners between the base portion of the shroud and the blades.
  • grooves into which the blades are to be inserted are formed in the annular groove formed in the shroud by the number corresponding to the number of the blades so that the impeller is formed by inserting the blades into these grooves.
  • cores each of -which has such a structure that, when the impeller has been formed by casting, neighboring blades partition the annular groove of the shroud are positioned on the circumference at a predetermined interval, fluid (e.g., molten alloy) is poured between the neighboring cores and between the core and the outer mold, and the fluid is solidified so that the impeller is manufactured.
  • fluid e.g., molten alloy
  • impeller component units each of which has neighboring blades and a part of the annular groove of the shroud formed therebetween are manufacture, and a plurality of these units are assembled to each other on the circumference so that the impeller is manufactured.
  • the blades are made of thin and light material.
  • the method of manufacturing an impeller according to the present invention is characterized in that the impeller is manufactured by manufacturing only the blades so as to have different shapes and coupling the thus manufactured blades and the shroud.
  • reference numeral 1 represents an impeller
  • 2 represents a casing forming an annular passage 8
  • 4 represents a motor for rotating the impeller 1.
  • the impeller 1 and the casing 2 are formed to face each other and the impeller 1 is fastened in such a manner that it can rotate with respect to the casing 2.
  • the motor 4 is placed on the base member 7a in such a manner that the motor 4 is secured to both the base member 7a and the casing 2.
  • An end of the annular passage 8 is communicated to an inlet passage 6a and the other end of the same is communicated to an outlet passage (not shown in Fig. 1).
  • the inlet passage 6a and the outer passage are formed in a muffler 7 which also serves as a base member.
  • the annular passage 8 is formed in an annular shape around the rotational center of the impeller 1, that is, around the rotational shaft 3 of the motor 4, the cross sectional shape of the annular passage 8 forming a semicircular arc when it is cut by a plane passing through the axial center of the rotational shaft 3.
  • a partition wall is formed between an inlet port and an outlet port each of which is communicated with the annular passage 8, the partition wall being formed with a small gap maintained for the purpose of permitting a plurality of blades 5 formed in the impeller 1 to pass through. Thus, the communication between the inlet port and the outlet port is prevented by the partition wall.
  • the impeller 1 is constituted by a wheel 9 and a shroud 11 which are secured to the rotational shaft 3 of the motor 4 and are capable of rotating with integrated to each other.
  • the shroud 11 has a passage 10 formed therein, the passage 10 having a multiplicity of blades 5 formed in a direction traversing the passage 10.
  • the shape of the blade 5 is, as shown in Figs. 2 to 6, formed in such a manner that at least the inner portion thereof has a three dimensional shape.
  • the air flow in the annular passage 8 will be described before it is explained about the shape of the blade 5.
  • the air flow in the annular passage 8 becomes as shown in Figs. 7 to 11.
  • Air introduced through an inlet port 6c passes, as shown in Figs. 7 and 8, through a passage 2a in the casing 2 formed in the impeller 1, the passage 2a being in the form of a circular cross sectional shape.
  • the air passes through the passage 2a while swirling around the center of the circular cross section and the pressure of which is being raised due to the rotation of the blades 5 until it reaches the outlet port through which the air is discharged.
  • the distribution of speed of air passing through the annular passage 8 after it has been introduced through the inlet port 6c with respect to the speed of the blade 5 becomes as shown in Fig. 10. That is, the speed of internal flow becomes positive values with respect to the direction of rotation of the impeller 1 in the region from the outer end 5a to a position near the central portion 5c, while it becomes negative values in the region from the position near the central portion 5c to the inner end 5b.
  • angle ⁇ 3 in the circumferential direction is determined so as to retract the blade 5 to the central portion 5c at the inner portion thereof, thereby making the internal flow uniform.
  • the speed distribution of the flow passing through the annular passage 8 in the traverse direction toward the rotational shaft 3 has, as shown in Fig. 11, speed vector running toward the casing 2 in a region from the outer end 5a to a position near the central portion 5c, and it has speed vector running toward the impeller 1 in the region from the position near the central portion 5c to the inner end 5b.
  • the axial inlet angle of the blade 5 is determined so as to be adapted to the resultant vector of the speed vector of the air passing though the annular passage 8 with respect to the blade 5 as shown in Fig. 10 and the speed vector of the air passing in the traverse direction toward the rotational shaft 3 with respect to the blade as shown in Fig. 11, that is, the vector w; in the speed triangle shown in Fig. 14.
  • the resultant speed vector changes in such a manner that the inlet angle of the front edge of the blade 5 is about 90 degrees at the inner end 5b and it becomes smaller in going toward the central portion 5c, so that the axial inlet angle is determined so as to be adapted to this change.
  • a shaft hole 20 for fastening the rotational shaft 3 is formed in a central portion of the impeller 1.
  • the impeller 1 has blades 5 and passages 10 between the blades 5 formed annularly in a space between radii R 1 and R 2 from the center of the shaft hole 20.
  • the structure is arranged in such a manner that the cross sectional shape, which is obtained by cutting the passages 10 between the blades 5 with a plane passing through the center of the shaft hole 20, forms a semicircular arc.
  • the cross sectional shape of the blade 5 is formed so as to be adapted to the aforesaid resultant speed vector of air in such a manner, for example, as shown in Figs. 2 to 6.
  • the inlet angle at the inner end 5b of the blade 5 is ⁇ 1 and the inlet angle at the position 5c is ⁇ c, both ⁇ 1 and ⁇ c being smaller than 90 degrees and having the different values from each other with a relationship of ⁇ 1 > y c held and, under this assumption, the blade 5 is formed by smoothly curved surface.
  • the axial exit angle y is formed to be 90 degrees in a region from the central portion to the outer portion.
  • the front edge of the blade 5 is formed in such a manner that it is delayed with respect to the direction of the rotation of the impeller 1 in the region from its inner end to a position slightly outer than the midpoint and it extends radially with respect to the center of the shaft hole 20 in the region outer than the above-described region. That is, as shown in Fig. 3 it is arranged in such a manner that the angle ⁇ 1 formed between the line tangent to the inner end 5b and the line connecting the midpoint 5c and the inner end 5b is less than 90° and the angle Q2 formed between the line tangent to the outer end 5a and the line connecting the midpoint 5c and the outer end 5b is 90 ⁇ .
  • the reason for this lies in that the direction of air flow is inverted at a portion slightly outer than the central portion.
  • the "axial angle y" is defined, here, to be an angle formed by the smoothly curved surface in the rotational direction side of the front edge portion of the blade 5 with respect to the plane in the front edge of the blade 5. Alternatively, it may be defined with respect to the center line of the cross section of the blade 5.
  • angle ⁇ in the circumferential direction is defined to be an angle which is in the opposite direction to the direction of rotation, among the angles formed - at the intersections between concentric circles with respect to the axial center of the impeller 1 and the front edge of the blade 5 - between the lines tangent to the above-described circles and the above-described front edge.
  • the air which has reached the outer portion changes in its flowing direction due to the axial exit angle of 90 degrees, so that the direction of the internal flow is changed into the forward direction with respect to the circumferential direction and, as a result, the work is given to the fluid from the blade 5 by one swirl, thereby causing the pressure of air to be raised.
  • a smooth internal flow passing along the blade 5 can be formed three dimensionally in at least the inside portion without any significant speed reduction, so that a flow having no excessive swirls and stagnation can be created.
  • the discharge pressure can be raised and a vortex flow blower whose noise is low can be obtained.
  • Fig. 15 illustrates the ratios between the pressure coefficients in the present invention and those of the conventional example when the value of ⁇ 1 of the impeller 1 according to the present invention is varied as 100, 90, 80, 60, 45 and 20 degrees and that of -y of the same is varied as 10, 20, 45, 70, 80 and 90 degrees.
  • the pressure coefficient ⁇ 0 of the conventional example is obtained when all of ⁇ 1 , A 2 , ⁇ i, ⁇ c and ⁇ 0 are 90 degrees.
  • the value of ⁇ c when obtaining the pressure coefficient ⁇ in an embodiment of the present invention was set to a value which is smaller than ⁇ c by 13 degrees.
  • the value of ⁇ 2 was fixed to 90 degrees and the value of Ri/R 2 to a constant value of 0.58.
  • the pressure coefficient is higher than that of the conventional example. If it is somewhat larger than 1.7, the pressure coefficient corresponds to 14 or more.
  • the pressure coefficient can be increased to a value higher than 14 when ⁇ 1 is 45 to 80 degrees, ⁇ i is 20 to 70 degrees and ⁇ c is smaller than ⁇ i by 13 degrees.
  • Fig. 16 illustrates the values of the pressure coefficient ratio when the value of ⁇ 2 was set to 70 degrees.
  • the pressure coefficient ratio obtainable when ⁇ 2 is 70 degrees is smaller than that when Q 2 is 90 degrees.
  • the pressure coefficient in this case is larger than that according to the conventional example when ⁇ 1 is 15 to 80 degrees, ⁇ i is 20 to 70 degrees and ⁇ c is smaller than ⁇ ; by 13 degrees.
  • Fig. 17 illustrate the relationship between the flow rate coefficient ⁇ and pressure coefficient 0 in each of the embodiment of the present invention and the conventional vortex flow blower. It can be understood that both the flow rate coefficient and the pressure coefficient in the embodiment of the present invention are higher than those in the conventional one.
  • Fig. 18 illustrates the relationship between the flow rate coefficient ⁇ and the pressure coefficient when the inlet angle ⁇ 1 in the circumferential direction is set to 20 degrees and 90 degrees. As seen from this drawing, both the flow rate coefficient and the pressure coefficient are higher when the inlet angle ⁇ 1 , in the circumferential direction is set to 20 degrees.
  • Fig. 19 illustrates the ratios of the pressure coefficients when the inlet angle ⁇ 1 in the circumferential direction is varied.
  • the exit angle ⁇ 2 in the circumferential direction is fixed to 90 degrees and they are compared with the case in which both ⁇ 1 and Q 2 are 90 degrees.
  • Fig. 20 illustrates the ratios of the pressure coefficients in the case where the axial inlet angle ⁇ 1 in the front edge of the blade 5 is varied with both ⁇ 1 and ⁇ 2 set to 90 degrees, as a standard in the case where both ⁇ 1 and Q 2 is set to 90 degrees. As seen from this drawing, the lesser the value of -yi is, the larger becomes the pressure coefficient ratio.
  • At least the axial inlet angle in the inner portion in the front edge of the blade 5 and the inlet angle in the circumferential direction are determined so as to be adapted to the resultant vector of the speed vector of the air flow passing through the annular passage 8 and the speed vector of the air flow passing in the traversing direction toward the rotational shaft in the annular passage 8 and thereby to form the three dimensionally shaped blades. Therefore, turbulence of the internal flow such as swirls and stagnation of air introduced into the internal portion can be satisfactorily prevented and, as a result, the aerodynamic performance can be significantly improved in comparison with the conventional vortex flow blower.
  • an advantage can be obtained in that the aerodynamic performance can be significantly improved by forming the inner portion of the blade into a three dimensional shape which can be adapted to the flow of fluid.
  • the drawback inherent in the conventional vortex flow blower in that the pressure coefficient is inevitably reduced when the ratio R i /R 2 is reduced to 0.75 or less for the purpose of reducing the size of the vortex flow blower can be overcome. Therefore, even if the ratio R 1 /R 2 is set to 0.75 or less and 0.3 or more, the discharge pressure can be significantly increased in comparison with the conventional vortex flow blower and, as a result, an advantage can be obtained in that the outer diameter of the impeller can be reduced and the size of the vortex flow blower can thereby be reduced.
  • the shape of the blade 5 from the inner portion to the central portion thereof is formed as shown in Figs. 2 and 3.
  • the speed distribution of air with respect to the speed of the blade 5 in the annular passage 8 becomes, as shown in Fig. 10, positive values with respect to the direction of the rotation of the impeller 1 and, in the portion from the central portion 5c to the outer end 5a, the speed component in the annular passage 8 becomes steeply increased in the forward direction with respect to the direction of the rotation of the blades 5. Therefore, the shape of the blade facing the annular passage 8 is formed to project from the central portion 5c to the outer end 5b in the direction of the rotation of the blade 5.
  • the exit angle ⁇ 2 in the circumferential direction is determined to 90 degrees or more in order to make the air flow on the outer side uniform by forming the blade 5 in such a manner that it projects from its central portion 5c toward the outer end 5a.
  • the axial outlet angle -y is determined so as to be adapted to the vector w o in the speed triangle shown in Fig. 12.
  • the shape of the blade 5 is formed by smoothly curved surface (see Figs. 22 to 26) formed in such a manner that both ⁇ c and ⁇ i are smaller than 90 degrees and the relationships of ⁇ e > ⁇ c and ⁇ i > ⁇ c are met, as shown in Figs. 24 to 26 and 27.
  • Air introduced so as to be adapted to the inlet flow including the counter flow component in the circumferential direction and having reached the outer portion changes the direction of the internal flow into the forward direction between the blades 5 since the axial exit angle ⁇ o is provided. Furthermore, since the exit angle 6 2 in the circumferential direction is provided, the slow speed flow near the midpoint and the high speed flows in the vicinity of the outer and inner ends of the blade 5 can be synchronized with one another. As a result, stagnation causing internal loss can be prevented, the swirling component can be incread- ed and the change in air speed between the blades 5 can be reduced.
  • the axial exit angle ⁇ o and the exit angle ⁇ 2 in the circumferential direction are provided as described above, the work obtainable by one swirl of the blade 5 can be made larger and the internal loss taken place in the action of the blade 5 can be restricted. As a result, the obtainable pressure can be raised.
  • the exit angle ⁇ 2 in the circumferential direction causes, between the blades, the flow near the midpoint whose internal speed is slow and the flows in the vicinity of outer and inner ends of the blade 5 whose internal speeds are high to be synchronized with one another. As a result, turbulence of the flow owing to stagnation, which causes the internal pressure loss, can be prevented.
  • the blade 5 acts to form a three dimensional smooth internal flow whose change in speed can be reduced in the passage 8, so that the aerodynamic performance exhibiting a significantly high pressure can be obtained.
  • the pressure coefficient becomes larger in comparison with the conventional vortex flow blower. Because of the above-described reason, with respect to the embodiment shown in Fig. 23 the pressure coefficient can be significantly improved by simultaneously changing the axial exit angle ⁇ o to 45 degrees and the exit angle Q2 in the circum- ferenfial direction to 115 degrees.
  • Fig. 32 is a map showing the pressure coefficient ratios when the axial exit angle ⁇ o and the exit angle ⁇ 2 in the circumferential direction are varied. As seen from this map, the pressure coefficient ratio can be significantly improved in the regions of 10° ⁇ ⁇ 2 ⁇ 135° and 20 * ⁇ o ⁇ 70°.
  • Fig. 33 is a graph which illustrates the experimental results when the outer portion of the blade 5 is three dimensionally formed in addition to the inner portion of the same which has been three dimensionally formed. As seen from this graph, the pressure coefficient can be further improved by three dimensionally forming the blade 5 as a whole, thereby making it possible to obtain a pressure coefficient of about 25.
  • the impeller 1 is, as shown in Fig. 23, arranged to have the blade 5 whose shape at the front edge is formed in such a manner that its central portion 5c connecting the inner portion and the outer portion of the blade 5 is steeply changed in its angle, but as shown in Fig. 34 the shape of the blade may be modified in such a manner that the angle is gradually changed from the inner end 5b to the outer end 5a.
  • the blade 5 is retracted with respect to the direction of the rotation of the impeller 1 in the inner side of the blade 5, while it is radially set or forwarded in the portion outer than the midpoint 5c, but as shown in Fig. 35 in the case where the blade 5 has been three dimensionally formed the front edge shape of the blade may be arranged to have such a shape as shown by symbols d and f in its inner portion and such a shape as shown by symbols a and c in its outer portion. Alternatively, these shapes shown by symbols a-c and d-f may combined.
  • the front edge of the outer portion of the blade 5 is arranged to have the curve c shown in Fig. 35. That is, the cross section of the outer portion of the blade 5 is retracted with respect to the direction of the rotation of the impeller 1 as shown in Fig. 38 in comparison with position of that shown in Fig. 23.
  • the blade is formed such that the axial edge -y in the inner portion becomes, as shown in Fig. 40, an angle which is similar to ⁇ i shown in Fig. 26, that the angle in the central position becomes slightly smaller than 90 degrees as shown in Fig. 39 and that the axial exit angle in the outer portion becomes larger than 90 degrees as shown in Fig. 38.
  • the blade 5 is formed in such a manner that the axial inlet angle ⁇ i is set to an angle similar to that shown in Fig. 23.
  • the blade 5 is further formed to have at its central position 5c such an axial angle ⁇ c as shown in Fig. 43 and to have an intermediate portion 32 retracting with respect to the direction of the rotation of the impeller 1 as shown in Fig. 41.
  • the outer portion of the blade 5 is formed to have the axial exit angle ⁇ o which is larger than 90 degrees as shown in Fig. 42.
  • FIG. 35 is a partial front elevational view which illustrates the impeller 1 according to this embodiment.
  • the blade does not appear as a section, it is illustrated with hatching for the purpose of having the torsional direction understood easily.
  • the parts given the same reference numerals as those shown in Fig. 3 are the same parts.
  • Fig. 46 illustrates cross sectional shapes of the blade at the radii B, C, D, E and F of Fig. 45.
  • the outer shape (cross sections B and C) of the blade 5 is formed in such a manner that the axial exit angle " ( 2 in the front edge 35 of the blade 5 is larger than 90 degrees.
  • the shape of the blade 5 is formed in such a manner that it forms a projecting curve in the direction opposite to the direction of the rotation with respect to a line connecting G and H.
  • the front edge 35 of the blade 5 is formed in its inner portion (cross sections E and F) in such a manner that it projects with respect to the direction of the rotation.
  • the shape of the blade 5 is formed in such a manner that it forms a projection curve in the direction of the rotation with respect to a line connecting H and I and, furthermore, the axial inlet angle -yi is smaller than 90 degrees. Furthermore, the front edge 35 of the blade 5 projects by etc in the direction of the rotation with respect to a radiant line relative to the axial center on cross section D in the central portion.
  • the axial inlet angle -yi in the front edge of the blade 5 in its inner portion is formed to be substantially the same as the incidental angle ⁇ a1 of the flow and the axial inlet angle ⁇ 1 in the front edge of the blade 5 is, on the other sections (sections D and E) in the inner portion of the blade 5, set to be adapted to the incidental angles ⁇ e1 and yd, which differ from each other in the degree and the direction, swirls and stagnation can be reduced. Since the outer portion is formed as shown in section B of Fig.
  • the discharge pressure can be controlled to a predetermined value.
  • Fig. 47 illustrates the shape of a partition wall 25 for partitioning the inlet port and the outlet port formed in the casing 2, the partition wall being capable of significantly eliminating noise.
  • the casing 2 has a circular arc passage 8 whose cross section facing in the direction running parallel to the axial line of the rotational shaft 3 is in the form of a semicircular arc groove.
  • the groove is provided with a partition wall 25 in a part thereof, the partition wall 25 facing the impeller 1 with a small gap retained therebetween.
  • An end of the circular arc passage 8 is connected to the inlet side passage 6a and the other end of the same is connected to the discharge side passage 6b.
  • the inlet side passage 6a and the outlet side passage 6b are provided to run parallel to each other in the muffler 7 which also serves as the base member.
  • a guide 26 adjacent to the inlet port is provided in a portion of the partition wall 25 adjacent to the inlet port.
  • a front portion 26a of the guide 26 adjacent to the inlet port is arranged to be substantially horizontal so as to make the blade 5 cut (intersect the front edge of the blade 5) from outside. It is considered that the front portion 26a acts to smoothly introduced air, which has been introduced into the circular arc passage 8 through the inlet port 6c, to the inlet port (the portion in which the arrows face the left hand direction in Fig. 11) of the blade 5.
  • the inlet port 6c When viewed from the axial direction, the inlet port 6c is hidden behind the guide 26 adjacent to the inlet port. This acts to prevent noise generated in the circular arc passage 8 from being directly transmitted to the passage 6a adjacent to the inlet port for the purpose of insulating noise.
  • a guide 28 adjacent to the outlet port is provided with the partition wall 25 adjacent to the outlet port.
  • the front end 28a of the guide 28 adjacent to the outlet port is formed in such a manner that its substantially central portion 28b (the portion which agrees with a point of the blade 5 at which the flow is inverted) projects in the direction opposite to the direction F of the rotation of the impeller 1 so as to make the blade 5 cut (intersect the front edge of the blade 5) from inside. It is considered that the front end 28a acts to guide air to be discharged from the circular arc passage 8 to the outlet port 6d so as to be smoo- thy discharged from the outlet portion (the portion in which arrows face the right hand direction in Fig. 11) of the blade 5.
  • the outlet port 6d when viewed from the axial direction, is substantially hidden behind the guide 28 adjacent to the outlet port. This acts to prevent noise generated in the circular arc passage 8 from being directly transmitted to the passage 6b adjacent to the outlet port for the purpose of insulating noise.
  • Fig. 48 is a graph which illustrates data about noise actually measured when a vortex flow blower composed by combining the casing 2 shown in Fig. 47 and the impeller 1 shown in Fig. 36 is operated.
  • the guide 28 adjacent to the inlet port and the guide 26 adjacent to the outlet port significantly assist to reduce noise when compared with noise data shown in Fig. 48 in the case where the vortex flow blower from which the guide 26 adjacent to the inlet port and the guide 28 have been removed is operated.
  • FIG. 49 An another embodiment of the present invention is shown in Fig. 49.
  • the impeller 1 having the blades 5 is disposed on the side adjacent to the motor 4 and the casing 2 is disposed to face the impeller 1.
  • the degree of the overhang of the impeller 1 can be reduced.
  • the impeller 1, which is a body of rotation is disposed adjacent to the bearing portion, vibrations of the impeller 1 can be significantly reduced, thereby causing the durability against the radial loads to be improved.
  • FIG. 50 is a perspective view which illustrates the vortex flow blower in which the double blade impeller is mounted.
  • the casing 2 is formed so as to cover the both sides of the double blades.
  • the annular passage 8 is formed on both sides of the double blades. Partition walls are provided on both sides of the casing 2 so as to hinder the communication between the outlet port 6d and the inlet port 6c.
  • the inlet side passage 6a and the outlet side passage 6b are provided adjacent to the motor 4.
  • a vortex flow blower exhibiting a high pressure coefficient and capable of obtaining a large wind quantity can be provided. Furthermore, another effect can be obtained in that the outer diameter of the casing can be reduced and the size of the vortex flow blower can thereby be reduced.
  • FIG. 55 to 63 An embodiment of the impeller is shown in Figs. 55 to 63.
  • the blade 5 as shown in Figs. 64 to 66 and the shroud 11 are independently formed. Then, the shroud 11 having the annular groove 45 and a plurality of blades 5 are coupled and secured to each other so that the impeller 1 is manufactured.
  • the shroud 11 can be manufactured by using a mold formed two dimensionally, so that it becames possible to be mass- produced by the die-casting or metal mold casting process. Further, even if the blade 5 is in the form of a complicated shape, it becomes possible to be die-cast or press-formed, so that the impeller having the three dimensionally shaped blades can be easily manufactured.
  • the blade 5 can be made of a thin and light weight material since the blades 5 are independently manufactured as described above. Therefore, an effect can be obtained in that the secondary moment of inertia of the impeller can be reduced.
  • the shroud 11 in which the annular groove 45 is formed and a plurality of insertion holes 40 are formed, and the blade 5 provided with a plurality of caulking projections 41 are manufactured.
  • the shroud 11 and the blade 5 are coupled to each other in such a manner that the caulking projections 41 formed on the blade 5 are inserted into the insertion holes 40 formed in the shroud 11, and then they are secured by plastically working the caulking projections 41.
  • the method of plastically working may be a cold working or a hot working. It is preferable in terms of the appearance after subjected to the plastic working that the following method be employed: namely, as shown in Fig. 57 an upper electrode 42 having a predetermined conductivity and high temperature strength and a lower copper electrode 43 are used and only the caulking projections 41 are plastically worked with heat generated by an electric current being applied thereto.
  • the blade 5 can be stabilized and further satisfactorily plastically deformed at the time of caulking, so that the airtightness between the blades 5 can be also improved.
  • Figs. 59 and 60 illustrate the cross sectional shape of the impeller which has been cut in the circumferential direction relative to the rotational center.
  • an insertion groove 44 having a width which is slightly narrower than the width of the blade 5 is formed in the annular groove 45 formed in the shroud 11.
  • the blade 5 is press-fitted into the insertion groove 44.
  • the fastening force can be further increased when the blade 5 having the caulking projections 41 is press-fitted and the caulking projections 41 are plastically worked.
  • the corner portions between the blades 5 and the shroud 11 may be filled with a filler 46 as shown in Fig. 61. Since the filler 46 acts to permit air to smoothly flow in addition to improving the airtightness, it is preferable from a view point of improving the aerodynamic performance. As shown in Fig. 62, the filler 46 can be easily formed by brazing the blade 5, to which a skin material 47 of the low melting point has been brazed, in a furnace.
  • FIG. 63 An another embodiment is shown in Fig. 63.
  • the impeller 1 in which the blade 5 has been secured to the shroud 11 by being press-fitted or by caulking its projections, is ultrasonic soldered in a jet type soldering tank 17 provided with a ultrasonic oscillator 16 while rotating the impeller 1, an oxide film formed on the surface to be soldered is broken by the supersonic erosion action, so that the application of the flux becomes unnecessary, thereby making it possible to efficiently manufacture the impeller 1 exhibiting excellent airtightness.
  • An another manufacturing method can be employed in which an adhesive is applied to the insertion groove 44 formed in the annular groove 45.
  • the shape shown in Fig. 61 can be easily formed. That is, when the blade 5 is press-fitted into the insertion groove 44 formed in the shroud 11, a part of the adhesive overflows to the corner portion and solidifies, thereby causing an effect similar to that obtainable when the filler has been filled.
  • impellers of complicated shapes can be easily manufactured and the thus obtained impellers can exhibit satisfactory airtightness.
  • the shroud 11 may be secured to the wheel 9 by a screw 48 or it may be secured as shown in Figs. 68 and 70 in such a manner that a part of the blade 5 is expanded so as to become an expansion portion 49 and a screw hole 50 is formed in the expansion portion 49 so as to be secured by the screw 48. It is preferable in terms of the performance that the expansion portion 49 be formed on the back side of the blade 5.
  • a ring 51 connecting the outer front end of the blade 5 is manufactured integrally with the blade 5 and the wheel 9, and the shroud 11 is, as shown in Fig. 69, inserted between the ring 51 and the wheel 9 so as to be secured.
  • the wheel 9 may be integrally formed as a whole or only a part of the wheel 9 may be integrally formed with the blade 5.
  • the mold can, of course, be manufactured easily and the mold can be readily removed after the casting has been completed. Therefore, impellers of a complicated shape can be readily manufactured.
  • annular groove 45 in such a manner that its width becomes smaller than that of the blade 5 and to provide the blade 5 in the groove 45 by inserting it while being elastically deformed, by using the adhesive or by using the filler.
  • cores 55 each of which has a shape partitioning the annular groove with the neighboring blades 5 are first manufactured.
  • the thus manufactured cores 55 are positioned at a predetermined interval away from each other on the circumference and are placed in an outer mold 58 having a circular groove 57 formed therein.
  • parts of the neighboring cores that is, a projection 59 of either core 55 and a notch 60 of the neighboring core 55 are disposed to overlap each other at a certain interval.
  • the reference numeral 61 represents a lower mold.
  • the blade 5 and the shroud 11 can be integrally formed.
  • the wheel 9 is integrally formed by a space 63.
  • the core 55 be made a shell core.
  • the core 55 may be made of silicone rubber.
  • the core 55 is constituted by a first portion 65 positioned behind a core neighboring either core 55, a second portion 66 positioned behind a core 55 neighboring the other core 55, and a third portion 67 positioned between the first portion 65 and the second portion 66 and not positioned behind any core 55.
  • the third portion 67 is firstly drawn out, and then the first portion 65 and the second portion 66 are drawn out so that the impeller is formed.
  • the first advantage according to the present invention can be obtained from the blade formed in such a manner that at least its inner portion is three dimensionally formed, thereby causing air to be smoothly introduced so as to be adapted to the speed vector of the swirling air flow. As a result, the discharge pressure can be significantly raised.
  • the second advantage can be obtained from the blade formed in such a manner that its shape is three dimensionally formed so as to be adapted to the speed vector of the swirling flow. Therefore, swirls and stagnation can be significantly prevented. As a result, a low noise vortex flow blower can be obtained.
  • the third advantage can be obtained from the partition wall formed in such a manner that its front end adjacent to the inlet port of the vortex flow blower is cut by the blade from the outside while the front end of the same adjacent to the outlet port is cut by the blade from the inside. Therefore, the air flow from the inlet port to the circular arc passage and the air flow discharged from the circular arc passage through the outlet port can be made smooth. As a result, noise can be extremely reduced.
  • the fourth advantage can be obtained from the blade formed in such a manner that the shape of the blade in the impeller is three dimensionally formed as mentioned before and Ri/Rz can thereby be set to 0.75 or less and 0.3 or more. As a result, the size of the vortex flow blower can be reduced.
  • the fifth advantage can be obtained from the blade formed in such a manner that the shape of the blade at the outer portion of the impeller is retracted and the axial outlet angle is arranged to be 90° or more. Therefore, work given by the blade to air can be restricted. As a result, the discharge pressure and the required operating power can be controlled to a low level.
  • the sixth advantage can be obtained from the method of manufacturing an impeller, which is constituted in such a manner that the blade and the shroud are independently manufactured and then they are coupled to each other. Therefore, impeller of a complicated shape can be readily manufactured.
  • the airtightness can be improved and the flow can be made smooth by using a filler or an adhesive.
  • the seventh advantage lies in that the secondary moment of inertia of the impeller can be reduced and the starting torque required for the motor can be reduced since the blade can be independently manufactured and made of a thin and light material.
  • the eighth advantage lies in that impellers of different shapes can be readily manufactured since only the blade can be independently manufactured and, as a result, impellers of different aerodynamic performance can be readily manufactured.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP90102729A 1989-02-13 1990-02-12 Wirbelstromgebläse und Verfahren zu dessen Herstellung Expired - Lifetime EP0383238B1 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
JP31033/89 1989-02-13
JP1031033A JPH02215997A (ja) 1989-02-13 1989-02-13 羽根車、及びその製造方法
JP51390/89 1989-03-03
JP5139089 1989-03-03

Publications (3)

Publication Number Publication Date
EP0383238A2 true EP0383238A2 (de) 1990-08-22
EP0383238A3 EP0383238A3 (de) 1991-10-16
EP0383238B1 EP0383238B1 (de) 1997-11-19

Family

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EP90102729A Expired - Lifetime EP0383238B1 (de) 1989-02-13 1990-02-12 Wirbelstromgebläse und Verfahren zu dessen Herstellung

Country Status (3)

Country Link
EP (1) EP0383238B1 (de)
KR (1) KR940007889B1 (de)
DE (1) DE69031713T2 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0506974A1 (de) * 1990-10-19 1992-10-07 Hitachi, Ltd. Laufrad für wirbelstromgebläse und verfahren zur herstellung dieses laufrades
EP0612923A1 (de) * 1993-02-23 1994-08-31 Hitachi, Ltd. Wirbelstromgebläse und Schaufelrad
WO1997010440A1 (de) * 1995-09-15 1997-03-20 Siemens Aktiengesellschaft Verdichteraggregat
DE19955955A1 (de) * 1999-11-19 2001-06-13 Siemens Ag Seitenkanalmaschine
CN108479201A (zh) * 2018-04-19 2018-09-04 成都瑞柯林工程技术有限公司 从气相物中分离出液相和/或固相物的设备
US10273960B2 (en) 2013-10-14 2019-04-30 Continental Automotive Gmbh Impeller for a side channel flow machine in particular designed as a side channel blower
EP4209679A1 (de) * 2022-01-07 2023-07-12 Delphi Technologies IP Limited Flüssigkeitspumpe und laufrad dafür

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19638847C5 (de) * 1996-09-21 2006-01-26 J. Eberspächer GmbH & Co. KG Seitenkanalgebläse, insbesondere für die Verbrennungsluftzuführung bei einem Standheizgerät eines Kraftfahrzeugs
US7037066B2 (en) * 2002-06-18 2006-05-02 Ti Group Automotive Systems, L.L.C. Turbine fuel pump impeller

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GB718751A (en) * 1952-11-21 1954-11-17 Rowland Rodway A new or improved fan or impeller
GB733578A (en) * 1953-05-18 1955-07-13 Ind Fan & Heater Company Ltd Improvements in the construction of fans or impellers
US3095820A (en) * 1960-02-29 1963-07-02 Mcculloch Corp Reentry rotary fluid pump
US3147541A (en) * 1959-11-16 1964-09-08 Torrington Mfg Co Mixed-flow fan and method of making
GB983687A (en) * 1963-12-11 1965-02-17 Ametek Inc Centrifugal impellers and method of fabricating same
GB1155049A (en) * 1965-09-22 1969-06-11 Budd Co A Sheet Metal Rotor Assembly for Centrifugal Pumps or Radial-Flow Turbines
DE1703329A1 (de) * 1968-05-02 1972-03-09 Webasto Werk Baier Kg W Seitenkanalgeblaese
FR2145915A5 (de) * 1971-07-14 1973-02-23 Eberspaecher J
DE2400496A1 (de) * 1973-01-10 1974-07-11 British Gas Corp Umfangsgeblaese
DE2361851A1 (de) * 1972-12-18 1974-07-11 Hitachi Ltd Wirbelgeblaese
US3951567A (en) * 1971-12-18 1976-04-20 Ulrich Rohs Side channel compressor
DE3128625A1 (de) * 1980-07-21 1982-03-18 Hitachi, Ltd., Tokyo Wirbelstromgeblaese
DE3520218A1 (de) * 1984-06-08 1985-12-12 Hitachi, Ltd., Tokio/Tokyo Laufrad fuer ein radialgeblaese
DE3605852A1 (de) * 1986-02-22 1987-08-27 Gebhardt Gmbh Wilhelm Laufrad fuer einen radialventilator
DE8808920U1 (de) * 1988-07-12 1988-09-08 Kayser-Herold, Uwe, Dipl.-Ing., 3300 Braunschweig Seitenkanalmaschine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE309096C (de) *
DE892498C (de) * 1939-12-19 1953-10-08 Siemens Ag Laufrad fuer Umlaufpumpen
GB718751A (en) * 1952-11-21 1954-11-17 Rowland Rodway A new or improved fan or impeller
GB733578A (en) * 1953-05-18 1955-07-13 Ind Fan & Heater Company Ltd Improvements in the construction of fans or impellers
US3147541A (en) * 1959-11-16 1964-09-08 Torrington Mfg Co Mixed-flow fan and method of making
US3095820A (en) * 1960-02-29 1963-07-02 Mcculloch Corp Reentry rotary fluid pump
GB983687A (en) * 1963-12-11 1965-02-17 Ametek Inc Centrifugal impellers and method of fabricating same
GB1155049A (en) * 1965-09-22 1969-06-11 Budd Co A Sheet Metal Rotor Assembly for Centrifugal Pumps or Radial-Flow Turbines
DE1703329A1 (de) * 1968-05-02 1972-03-09 Webasto Werk Baier Kg W Seitenkanalgeblaese
FR2145915A5 (de) * 1971-07-14 1973-02-23 Eberspaecher J
US3951567A (en) * 1971-12-18 1976-04-20 Ulrich Rohs Side channel compressor
DE2361851A1 (de) * 1972-12-18 1974-07-11 Hitachi Ltd Wirbelgeblaese
DE2400496A1 (de) * 1973-01-10 1974-07-11 British Gas Corp Umfangsgeblaese
DE3128625A1 (de) * 1980-07-21 1982-03-18 Hitachi, Ltd., Tokyo Wirbelstromgeblaese
DE3520218A1 (de) * 1984-06-08 1985-12-12 Hitachi, Ltd., Tokio/Tokyo Laufrad fuer ein radialgeblaese
DE3605852A1 (de) * 1986-02-22 1987-08-27 Gebhardt Gmbh Wilhelm Laufrad fuer einen radialventilator
DE8808920U1 (de) * 1988-07-12 1988-09-08 Kayser-Herold, Uwe, Dipl.-Ing., 3300 Braunschweig Seitenkanalmaschine

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0506974A1 (de) * 1990-10-19 1992-10-07 Hitachi, Ltd. Laufrad für wirbelstromgebläse und verfahren zur herstellung dieses laufrades
EP0506974A4 (en) * 1990-10-19 1993-04-07 Hitachi, Ltd. Impeller for vortex flow blower and method of making said impeller
EP0612923A1 (de) * 1993-02-23 1994-08-31 Hitachi, Ltd. Wirbelstromgebläse und Schaufelrad
US5628615A (en) * 1993-02-23 1997-05-13 Hitachi, Ltd. Vortex flow blower and vane wheel therefor
WO1997010440A1 (de) * 1995-09-15 1997-03-20 Siemens Aktiengesellschaft Verdichteraggregat
DE19955955A1 (de) * 1999-11-19 2001-06-13 Siemens Ag Seitenkanalmaschine
US10273960B2 (en) 2013-10-14 2019-04-30 Continental Automotive Gmbh Impeller for a side channel flow machine in particular designed as a side channel blower
CN108479201A (zh) * 2018-04-19 2018-09-04 成都瑞柯林工程技术有限公司 从气相物中分离出液相和/或固相物的设备
CN108479201B (zh) * 2018-04-19 2024-06-07 成都瑞柯林工程技术有限公司 从气相物中分离出液相和/或固相物的设备
EP4209679A1 (de) * 2022-01-07 2023-07-12 Delphi Technologies IP Limited Flüssigkeitspumpe und laufrad dafür
US12000411B2 (en) 2022-01-07 2024-06-04 Phinia Delphi Luxembourg Sarl Fluid pump impeller including blades extending from a hub to an outer ring and having a draft angle between adjacent blades that varies between the hub and the outer ring

Also Published As

Publication number Publication date
EP0383238A3 (de) 1991-10-16
DE69031713T2 (de) 1998-06-04
EP0383238B1 (de) 1997-11-19
DE69031713D1 (de) 1998-01-02
KR940007889B1 (ko) 1994-08-27
KR900013215A (ko) 1990-09-05

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