WO1993001415A1 - Guide vane means - Google Patents

Guide vane means Download PDF

Info

Publication number
WO1993001415A1
WO1993001415A1 PCT/SE1992/000481 SE9200481W WO9301415A1 WO 1993001415 A1 WO1993001415 A1 WO 1993001415A1 SE 9200481 W SE9200481 W SE 9200481W WO 9301415 A1 WO9301415 A1 WO 9301415A1
Authority
WO
WIPO (PCT)
Prior art keywords
guide vanes
arrangement
fan
ring
alternate
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.)
Ceased
Application number
PCT/SE1992/000481
Other languages
French (fr)
Inventor
Vladimir Tupov
Patrik Nilsson
Börje Nilsson
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.)
ABB Technology FLB AB
Original Assignee
ABB Flaekt AB
Flaekt AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority to DE69224853T priority Critical patent/DE69224853T2/en
Priority to JP5501767A priority patent/JPH06509150A/en
Priority to RU94015165/06A priority patent/RU2101576C1/en
Priority to EP92915625A priority patent/EP0680563B1/en
Priority to KR1019940700027A priority patent/KR100229693B1/en
Priority to AU23312/92A priority patent/AU657353B2/en
Application filed by ABB Flaekt AB, Flaekt AB filed Critical ABB Flaekt AB
Priority to US08/175,356 priority patent/US5470200A/en
Priority to DK92915625T priority patent/DK0680563T3/en
Publication of WO1993001415A1 publication Critical patent/WO1993001415A1/en
Priority to FI940057A priority patent/FI102310B1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes

Definitions

  • the following invention relates to a guide vane arrangement for axial fans, intended to convert the rotational component in the gas flow velocity after passage through the impeller into a substantially axial velocity, the arrangement including a ring of guide vanes disposed downstream of the fan and in spaced relationship therewith.
  • the gas flow downstream of the impeller of an axial fan normally rotates.
  • the rotational energy can be translated into useful energy by a guide vane arrangement on the outlet side of the fan, this arrangement converting the rotational velocity to an axial velocity component.
  • the pressure is raised in this way, and the efficiency of the fan increases. Normally, how ⁇ ever, the sound level also increases at the same time.
  • the sound from a fan comprises tonal components, i.e. tones with discrete frequencies and a wide band noise with a continuous frequency spectrum.
  • tonal components i.e. tones with discrete frequencies and a wide band noise with a continuous frequency spectrum.
  • a guide vane is described in the Swedish patent 8802136-5, which has improved aerodynamic and acoustic properties.
  • Fig. 1 illustrates how the strength in an individual tone can be reduced by displacing the guide vanes in the circum ⁇ ferential direction of the guide vane ring. It will also be seen from the same figure that the noise at higher frequencies over about 500 Hz also increases at the same time.
  • the object of the present invention is to lower indivi ⁇ dual, disturbing tones in the fan sound, as well as lower the general noise level in a simple way.
  • the first-mentioned object is achieved with a guide vane ring of the kind mentioned in the introduction, and with characteristics disclosed in claim 1.
  • the second object is achieved by a further development of the inventive guide vane arrangement, in which alternate guide vanes are axially displaced relative the remaining ones, so that alternate guide vanes are at a first axial distance from the fan, and the remainder at a second axial distance, simulta ⁇ neously as the guide vanes are non-uniformly distributed in the guide vane ring circumference.
  • alternate guide vanes are displaced in the circumferential direction relative the remaining guide vanes with a constant displacement so that the distance in the circumferential direction between juxta ⁇ posed guide vanes alternates between two given values.
  • This arrangement reduces both individual tones and the general wide band noise from the fan.
  • this combination of axial displacement and circumferential displacement of the guide vanes provides improved efficiency of the fan, compared with the case using a guide vane arrangement with solely axial displacement of the guide vanes, or solely rotation of them in the circumferential direction.
  • the axial displacement of the guide vanes is in the interval 0,4 - 0,7 l/l ch , preferably 0,5 l/l ch , where 1 denotes the magnitude of the displacement and l ch the length along the guide vane.
  • the displacement in the circumferential direction is in the interval 5 - 15°, and is preferably 10°.
  • the guide vane ring arrangement is divided into two rings axially in tandem, alternate guide vanes being carried by one ring and the other guide vanes by the other ring, the rings being axially dis- placeable relative each other or radially rotatable relative each other about a common axis. It is thus possible to adjust the guide vane arrangement in a simple way to achieve optimum conditions.
  • the guide vanes are designed with a web configuration between the radially outer and inner portions of the guide vane such that the arcuate length along the single-curved guide vane at the level of the web is shorter than at said mentioned outer and inner portions.
  • Fig. 1 illustrates the effect on the sound level from the fan when alternate guide vanes are displaced in the circumferential direction in accordance with prior art
  • Fig. 2 illustrates an axial fan with guide vanes arranged downstream of the fan
  • Fig. 1 illustrates the effect on the sound level from the fan when alternate guide vanes are displaced in the circumferential direction in accordance with prior art
  • Fig. 2 illustrates an axial fan with guide vanes arranged downstream of the fan
  • Fig. 1 illustrates the effect on the sound level from the fan when alternate guide vanes are displaced in the circumferential direction in accordance with prior art
  • Fig. 2 illustrates an axial fan with guide vanes arranged downstream of the fan
  • Fig. 1 illustrates the effect on the sound level from the fan when alternate guide vanes are displaced in the circumferential direction in accordance with prior art
  • Fig. 2 illustrates an axial fan with guide vanes arranged downstream of the fan
  • FIG. 3 schematically illustrates five different guide vane arrange ⁇ ments: a) guide vanes arranged uniformly according to the prior art, b) alternate guide vanes displaced in the circumferential direction of the guide vane ring according to the prior art, c) alternate guide vanes axially displaced in accordance with the invention, d) a combination of axial displacement and rotation of the guide vane ring in a circumferential direction in accordance with the invention, e) the combination of the displacement in the circumferential direction and the provision of a cut-out in alternate guide vanes in accordance with the invention;
  • Fig. 4 illustrates the effect on the sound from the fan resulting from the axial displacement of the alternate guide vanes in accordance with the operational case c) in Fig. 3; Fig.
  • FIG. 5 illustrates the effect on the sound level from the fan of the combination of axial displacement and displacement of the guide vanes in the circumferential direction of the guide vane ring according to the operational case d) in Fig. 3;
  • Fig. 6 illustrates the reduction of sound in the tone at the blade frequency as a function of the rotation in the circum ⁇ ferential direction for a given axial displacement of the guide vanes;
  • Fig. 7 illustrates an embodiment of the arrangement where two guide vane rings are used and Fig. 8 illustrates a particular guide vane configuration.
  • Fig. 2 illustrates an axial fan installed in a duct 4 and having a guide vane ring 2 arranged in spaced relationship with, and downstreams of the impeller 1.
  • the number of guide vanes is preferably between 0,5 and 2,1 times the number of blades in the impeller.
  • Fig. 1 the effects on the sound from a fan with guide vane arrangements according to the principles shown in figs. 3a and 3b are compared under the conditions given above. It will be seen from Fig. 1 that displacement of alternate guide vanes in the circumferential direction of the guide vane ring accor ⁇ ding to Fig. 3b results in a heavy decrease of a tone at the blade frequency 160 Hz, while there is an increase in the noise level for frequencies over about 500 Hz.
  • Fig. 4 compares the effect on the sound level of the guide vane arrangements according to figs. 3a and 3c. It will be seen that there is a considerable lowering of a tone at the blade frequency 160 Hz of about 3,5 dB, while there is an increase of the wide band high frequency noise over about 500 Hz.
  • the operational conditions are the same as for Fig. 1.
  • Fig. 5 the sound levels for the guide vane arrangements according to figs. 3a and 3d are compared.
  • the surprising result will be seen from this figure that the combination of axial displacement and rotation in the circumferential direc ⁇ tion of the ring of alternate guide vanes leads to a reduction of the sound level over the entire frequency range, compared with a conventional guide vane arrangement with uniformly distributed guide vanes.
  • Fig. 5 demonstrates that both discrete tones at lower frequencies and the wide band high frequency noise are antenuated in an embodiment according to Fig. 3d.
  • Rotation in the circumferential direction amounts to 10°.
  • Fig. 6 there is illustrated the attenuation ⁇ L ⁇ at the blade frequency, as a function of the rotation 6 of alternate guide vanes in a guide vane arrangement where the alternate guide vane is also axially diplaced by half the length of the guide vane.
  • This diagram shows that considerable reduction of tonal compo ⁇ nents is achieved in the angle range 5-15° for the axial displacement of the guide vanes that is under consideration. Measurements have also shown that some improvement of the aerodynamic efficiency of the fan in the region where the best sound attenuation is achieved.
  • FIG. 3e Another acoustically advantageous embodiment of the appa ⁇ ratus according to the invention is illustrated in Fig. 3e.
  • a portion of the end part facing towards the impeller of alternate guide vanes is cut away, so that the forward edge of these guide vanes is at a first axial distance from the impeller and the remainder at a second axial distance.
  • the guide vanes are non-uniformly distributed round the circumference of the ring.
  • Fig. 7 there is illustrated a further advantageous embodiment of the guide vane ring 2 in the apparatus in accor ⁇ dance with the invention.
  • the ring 2 is made up from two rings 20,22 mounted on a common shaft.
  • alternate guide vanes are carried by one of the two rings and the other by the other ring.
  • the two rings are mutually axially displacable and relatively rotatable about the common shaft.
  • Fig. 8 illustrates an embodiment of a guide vane 6, which is found to be advantageous in the arrangement according to the invention.
  • the end portion of the guide vane 10, which is intended to face towards the impeller has an edge 10 with a parabola-like configuration, so that between the inner and outer longitudinal edges 12 and 14 of the guide vane 6 there is a web with a shorter length L 2 along the guide vane than said edges L ⁇ and L 3 , respectively.
  • the guide vane has a straight back edge 16. If the height of the web from the inner longitu ⁇ dinal edge 12 is denoted by ⁇ and the total height of the guide vane by H 2 the position of the web is determined by the condition: and preferably 0,5 ⁇ H--/ ⁇ ⁇ 0,8

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

A guide vane arrangement for axial fans, intended to translate the rotational component of the gas flow velocity after passage through the impeller (1) into a substantially axial velocity, including a ring (2) of guide vanes disposed downstream of the fan and in spaced relationship therewith. Alternate guide vanes are axially displaced with respect to the remaining ones, so that alternate guide vanes are at a first axial distance from the fan and the remainder are at a second axial distance from the fan. As an alternative, alternate guide vanes have a portion of the end part facing towards the fan removed, so that the forward edge of alternate guide vanes is at a first distance from the fan and the remaining guide vanes are at a second axial distance, and the guide vanes are non-uniformly distributed along the periphery of the ring.

Description

GUIDE VANE MEANS
The following invention relates to a guide vane arrangement for axial fans, intended to convert the rotational component in the gas flow velocity after passage through the impeller into a substantially axial velocity, the arrangement including a ring of guide vanes disposed downstream of the fan and in spaced relationship therewith.
The gas flow downstream of the impeller of an axial fan normally rotates. The rotational energy can be translated into useful energy by a guide vane arrangement on the outlet side of the fan, this arrangement converting the rotational velocity to an axial velocity component. The pressure is raised in this way, and the efficiency of the fan increases. Normally, how¬ ever, the sound level also increases at the same time.
The sound from a fan comprises tonal components, i.e. tones with discrete frequencies and a wide band noise with a continuous frequency spectrum. Considerable efforts have been made primarily to lower the tonal components, by suitable arrangement and embodiment of guide vanes on the output side of the fan.
It is accordingly a general understanding that the noise generated decreases with increasing distance between the impeller and guide vanes, see M.J. Benzakein, J. Acoust. Soc. Am. 51 (1972), 1427-1438 and W. Neise, Proc. INTER-NOISE 1988, pp 767-776. It has been found, however, this is not always applicable.
A guide vane is described in the Swedish patent 8802136-5, which has improved aerodynamic and acoustic properties.
It has also been found earlier that a non-uniform dis¬ tribution of the guide vanes in the ring of guide vanes can give rise to certain acoustic improvements, although it has been found that large deviations from a uniform distribution of the guide vanes give rise to aerodynamic problems.
It is also known that certain acoustic characteristics can be improved by a portion being cut out from alternate guide vanes in their the forward portions.
Fig. 1 illustrates how the strength in an individual tone can be reduced by displacing the guide vanes in the circum¬ ferential direction of the guide vane ring. It will also be seen from the same figure that the noise at higher frequencies over about 500 Hz also increases at the same time. The measure¬ ment has been made for a fan R.P.M. of n = 970 and a displace¬ ment of alternate guide vanes of jS = 10° and β = 0° .
The object of the present invention is to lower indivi¬ dual, disturbing tones in the fan sound, as well as lower the general noise level in a simple way.
The first-mentioned object is achieved with a guide vane ring of the kind mentioned in the introduction, and with characteristics disclosed in claim 1.
The second object is achieved by a further development of the inventive guide vane arrangement, in which alternate guide vanes are axially displaced relative the remaining ones, so that alternate guide vanes are at a first axial distance from the fan, and the remainder at a second axial distance, simulta¬ neously as the guide vanes are non-uniformly distributed in the guide vane ring circumference. Preferably, alternate guide vanes are displaced in the circumferential direction relative the remaining guide vanes with a constant displacement so that the distance in the circumferential direction between juxta¬ posed guide vanes alternates between two given values. This arrangement reduces both individual tones and the general wide band noise from the fan. In addition, this combination of axial displacement and circumferential displacement of the guide vanes provides improved efficiency of the fan, compared with the case using a guide vane arrangement with solely axial displacement of the guide vanes, or solely rotation of them in the circumferential direction.
By the combination of measures according to this further development of the apparatus in accordance with the invention, there are achieved highly important advantages, both in respect of acoustics and efficiency, considerably exceeding the effects achieved by the individual measures of axial displacement or circumferential rotation of the guide vanes.
In accordance with another advantageous embodiment of the inventive apparatus, the axial displacement of the guide vanes is in the interval 0,4 - 0,7 l/lch, preferably 0,5 l/lch, where 1 denotes the magnitude of the displacement and lch the length along the guide vane.
In accordance with yet another advantageous embodiment, the displacement in the circumferential direction is in the interval 5 - 15°, and is preferably 10°.
In accordance with a further advantageous embodiment of the apparatus in accordance with the invention, the guide vane ring arrangement is divided into two rings axially in tandem, alternate guide vanes being carried by one ring and the other guide vanes by the other ring, the rings being axially dis- placeable relative each other or radially rotatable relative each other about a common axis. It is thus possible to adjust the guide vane arrangement in a simple way to achieve optimum conditions.
In accordance with a further advantageous embodiment of the invention, in the portion facing towards the impeller the guide vanes are designed with a web configuration between the radially outer and inner portions of the guide vane such that the arcuate length along the single-curved guide vane at the level of the web is shorter than at said mentioned outer and inner portions.
Embodiments of the arrangements in accordance with the invention, selected as examples, will now be described in more detail and with reference to the accompanying drawings, where Fig. 1 illustrates the effect on the sound level from the fan when alternate guide vanes are displaced in the circumferential direction in accordance with prior art; Fig. 2 illustrates an axial fan with guide vanes arranged downstream of the fan; Fig. 3 schematically illustrates five different guide vane arrange¬ ments: a) guide vanes arranged uniformly according to the prior art, b) alternate guide vanes displaced in the circumferential direction of the guide vane ring according to the prior art, c) alternate guide vanes axially displaced in accordance with the invention, d) a combination of axial displacement and rotation of the guide vane ring in a circumferential direction in accordance with the invention, e) the combination of the displacement in the circumferential direction and the provision of a cut-out in alternate guide vanes in accordance with the invention; Fig. 4 illustrates the effect on the sound from the fan resulting from the axial displacement of the alternate guide vanes in accordance with the operational case c) in Fig. 3; Fig. 5 illustrates the effect on the sound level from the fan of the combination of axial displacement and displacement of the guide vanes in the circumferential direction of the guide vane ring according to the operational case d) in Fig. 3; Fig. 6 illustrates the reduction of sound in the tone at the blade frequency as a function of the rotation in the circum¬ ferential direction for a given axial displacement of the guide vanes; Fig. 7 illustrates an embodiment of the arrangement where two guide vane rings are used and Fig. 8 illustrates a particular guide vane configuration.
Fig. 2 illustrates an axial fan installed in a duct 4 and having a guide vane ring 2 arranged in spaced relationship with, and downstreams of the impeller 1. The number of guide vanes is preferably between 0,5 and 2,1 times the number of blades in the impeller.
In Fig. 1 the effects on the sound from a fan with guide vane arrangements according to the principles shown in figs. 3a and 3b are compared under the conditions given above. It will be seen from Fig. 1 that displacement of alternate guide vanes in the circumferential direction of the guide vane ring accor¬ ding to Fig. 3b results in a heavy decrease of a tone at the blade frequency 160 Hz, while there is an increase in the noise level for frequencies over about 500 Hz.
Fig. 4 compares the effect on the sound level of the guide vane arrangements according to figs. 3a and 3c. It will be seen that there is a considerable lowering of a tone at the blade frequency 160 Hz of about 3,5 dB, while there is an increase of the wide band high frequency noise over about 500 Hz. The operational conditions are the same as for Fig. 1.
In Fig. 5 the sound levels for the guide vane arrangements according to figs. 3a and 3d are compared. The surprising result will be seen from this figure that the combination of axial displacement and rotation in the circumferential direc¬ tion of the ring of alternate guide vanes leads to a reduction of the sound level over the entire frequency range, compared with a conventional guide vane arrangement with uniformly distributed guide vanes. Fig. 5 demonstrates that both discrete tones at lower frequencies and the wide band high frequency noise are antenuated in an embodiment according to Fig. 3d. The axial displacement of the guide vanes is l/lcn = 0,5, where 1 denotes the magnitude of the displacement and lch the length along the guide vane, i.e. the displacement amounts to half the length of the guide vane. Rotation in the circumferential direction amounts to 10°. The curves are measured for a fan R.P.M. of n = 970.
In Fig. 6 there is illustrated the attenuation ΔL^ at the blade frequency, as a function of the rotation 6 of alternate guide vanes in a guide vane arrangement where the alternate guide vane is also axially diplaced by half the length of the guide vane. The graphs are shown for two different revolutiona¬ ry velocities of the fan, namely n = 970 rpm, and n = 1430 rpm. This diagram shows that considerable reduction of tonal compo¬ nents is achieved in the angle range 5-15° for the axial displacement of the guide vanes that is under consideration. Measurements have also shown that some improvement of the aerodynamic efficiency of the fan in the region where the best sound attenuation is achieved.
Another acoustically advantageous embodiment of the appa¬ ratus according to the invention is illustrated in Fig. 3e. In this embodiment a portion of the end part facing towards the impeller of alternate guide vanes is cut away, so that the forward edge of these guide vanes is at a first axial distance from the impeller and the remainder at a second axial distance. In addition, the guide vanes are non-uniformly distributed round the circumference of the ring.
In Fig. 7 there is illustrated a further advantageous embodiment of the guide vane ring 2 in the apparatus in accor¬ dance with the invention. The ring 2 is made up from two rings 20,22 mounted on a common shaft. Here, alternate guide vanes are carried by one of the two rings and the other by the other ring. The two rings are mutually axially displacable and relatively rotatable about the common shaft. With this em¬ bodiment of the guide vane ring 2 there is enabled in a simple way the axial displacement and circumferential rotation of the guide vanes relative each other so that desired properties are achieved.
Fig. 8 illustrates an embodiment of a guide vane 6, which is found to be advantageous in the arrangement according to the invention. The end portion of the guide vane 10, which is intended to face towards the impeller has an edge 10 with a parabola-like configuration, so that between the inner and outer longitudinal edges 12 and 14 of the guide vane 6 there is a web with a shorter length L2 along the guide vane than said edges L^ and L3, respectively. The guide vane has a straight back edge 16. If the height of the web from the inner longitu¬ dinal edge 12 is denoted by ^ and the total height of the guide vane by H2 the position of the web is determined by the condition:
Figure imgf000008_0001
and preferably 0,5 < H--/^ < 0,8

Claims

1. Guide vane arrangement for axial fans, intended to translate the rotational component of the gas flow velocity after passage through the impeller into a substantially axial velocity, said arrangement including a ring of guide vanes arranged downstream of the fan and in spaced relationship therewith, characterised in that alternate guide vanes are axially displaced relative the remaining ones, so that alterna¬ te guide vanes are at a first axial distance from the fan and the remainder at a second axial distance.
2. Arrangement as claimed in claim 1, characterised in that the guide vanes are non-uniformly distributed along the circumference of the ring.
3. Guide vane arrangement for axial fans, intended to translate the rotational component of the gas flow velocity after passage through the impeller into a substantially axial velocity, said arrangement including a ring of guide vanes arranged downstream the fan and in spaced relationship there¬ with, characterised in that a portion of the end part facing towards the impeller of alternate guide vanes is cut away so that the forward edge of said guide vanes is at a first axial distance from the fan and the remainder of the guide vanes at a second axial distance, and in that the guide vanes are non- uniformly distributed along the circumference of the ring.
4. Arrangement as in either of claims 2 or 3, characteri¬ sed in that alternate guide vanes are displaced in the circum¬ ferential direction relative the remaining guide vanes, with a constant displacement, so that the distance in the circum¬ ferential direction between adjacent guide vanes varies between two given values.
5. Arrangement as claimed in either of claims 1 or 2, characterised in that the axial displacement is in the interval 0,4-0,7 l/lch, preferably amounting to 0,5 l/lcn where 1 denotes the magnitude of the displacement and lch the length of the guide vane.
6. Arrangement as claimed in any one of claims 2-5, cha¬ racterised in that the displacement in the circumferential direction is in the interval 5-15°, preferably 10°. 7. Arrangement as claimed in any one of 1-6, characterised in that the guide vane ring comprises two rings axially in tandem, alternate guide vanes being carried by one ring and the remainder by the other ring, and in that these two rings are mutually axially displaceable and/or radially rotatable relati¬ ve each other about a common axis.
8. Arrangement as claimed in any one of claims 1-7, cha¬ racterised in that the guide vanes, in the part facing towards the fan, are formed with a web between the radially outer and inner portions of the guide vane, the arcuate length along the single-curved guide vane at the level of the web being shorter than at said outer and inner portions.
9. Arrangement as claimed in any one of claims 1-8, cha¬ racterised in that the number of guide vanes is between 0,5 and 2,1 times the number of blades of the impeller.
AMENDED CLAIMS
[received by the International Bureau on 4 December 1992 (04.12.92) ; original claims 1-9 replaced by amended claims 1-9 (2 pages)]
1. Guide vane arrangement for axial fans, intended to translate the rotational component of the gas flow velocity after passage through the impeller (1) into a substantially axial velocity, said arrangement including a ring (2) of guide vanes arranged downstream of the fan and in spaced relationship therewith, characterised in that alternate guide vanes with the edge facing the impeller are axially displaced relative the remaining ones, so that alternate guide vanes are at a first axial distance from the fan and the remainder at a second axial distance, and in that the guide vanes are non-uniformly dis¬ tributed along the circumference of the ring.
2. Arrangement according to claim 1, characterised in that a portion of the end part facing towards the impeller (1) of alternate guide vanes is cut away so that the forward edge of said guide vanes is at a first axial distance from the fan and the remainder of the guide vanes at a second axial distan¬ ce.
3. Arrangement according to claim 1, characterized in that alternate guide vanes are axially displaced relative to the remaining guide vanes, so that the forward edge of alternate guide vanes are at first axial distance from the impeller and the remaining guide vanes are at a second axial distance.
4. Arrangement as in either of claims 2 or 3, characteri¬ sed in that alternate guide vanes are displaced in the circum¬ ferential direction relative the remaining guide vanes, with a constant displacement, so that the distance in the circum¬ ferential direction between adjacent guide vanes varies between two given values.
5. Arrangement as claimed in either of claims 1 or 2, characterised in that the axial displacement is in the interval 1/1-jjj = 0.4-0.7, preferably amounting to l/lcn = 0.5 where 1 denotes the magnitude of the displacement and lch the length of the guide vane.
6. Arrangement as claimed in any one of claims 2-5, cha¬ racterised in that the displacement in the circumferential direction is in the interval 5-15°, preferably 10°.
7. Arrangement as claimed in any one of 1-6, characterised in that the guide vane ring (2) comprises two rings (20,22) axially in tandem, alternate guide vanes being carried by one ring and the remainder by the other ring, and in that these two rings are mutually axially displaceable and/or radially rotat¬ able relative each other about a common axis.
8. Arrangement as claimed in any one of claims 1-7, cha¬ racterised in that the guide vanes, in the part facing towards the fan, are formed with a web between the radially outer and inner portions of the guide vane, the arcuate length along the single-curved guide vane at the level of the web being shorter than at said outer and inner portions.
9. Arrangement as claimed in any one of claims 1-8, cha¬ racterised in that the number of guide vanes is between 0.5 and 2.1 times the number of blades of the impeller.
PCT/SE1992/000481 1991-07-09 1992-06-26 Guide vane means Ceased WO1993001415A1 (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
JP5501767A JPH06509150A (en) 1991-07-09 1992-06-26 guide vane device
RU94015165/06A RU2101576C1 (en) 1991-07-09 1992-06-26 Axial-flow fan guide-vane assembly
EP92915625A EP0680563B1 (en) 1991-07-09 1992-06-26 Guide vane means
KR1019940700027A KR100229693B1 (en) 1991-07-09 1992-06-26 Guide vane construct
AU23312/92A AU657353B2 (en) 1991-07-09 1992-06-26 Guide vane means
DE69224853T DE69224853T2 (en) 1991-07-09 1992-06-26 GUIDE BLADE ELEMENTS
US08/175,356 US5470200A (en) 1991-07-09 1992-06-26 Guide vanes for axial fans
DK92915625T DK0680563T3 (en) 1991-07-09 1992-06-26 The guide vane arrangement
FI940057A FI102310B1 (en) 1991-07-09 1994-01-07 guide vane

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE9102150-1 1991-07-09
SE9102150A SE500471C2 (en) 1991-07-09 1991-07-09 Guide device in an axial fan

Publications (1)

Publication Number Publication Date
WO1993001415A1 true WO1993001415A1 (en) 1993-01-21

Family

ID=20383309

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE1992/000481 Ceased WO1993001415A1 (en) 1991-07-09 1992-06-26 Guide vane means

Country Status (13)

Country Link
US (1) US5470200A (en)
EP (1) EP0680563B1 (en)
JP (1) JPH06509150A (en)
KR (1) KR100229693B1 (en)
AU (1) AU657353B2 (en)
CA (1) CA2111103A1 (en)
DE (1) DE69224853T2 (en)
DK (1) DK0680563T3 (en)
ES (1) ES2113951T3 (en)
FI (1) FI102310B1 (en)
RU (1) RU2101576C1 (en)
SE (1) SE500471C2 (en)
WO (1) WO1993001415A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6803042B2 (en) 1993-10-29 2004-10-12 U.S. Army Medical Research Materiel Command Oral or intranasal vaccines using hydrophobic complexes having proteosomes and lipopolysaccharides
GB2401654A (en) * 2003-05-14 2004-11-17 Rolls Royce Plc A stator vane assembly for a turbomachine
DE102010002395A1 (en) * 2010-02-26 2011-09-01 Rolls-Royce Deutschland Ltd & Co Kg Turbofan engine comprises support strut which is provided as aerodynamically formed structural guide vanes opposite to aerodynamic guide vanes of larger blade thickness

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2808568B1 (en) * 2000-05-05 2002-08-02 Valeo Thermique Moteur Sa FAN FOR MOTOR VEHICLE PROVIDED WITH STEERING BLADES
US6471473B1 (en) 2000-10-17 2002-10-29 Rule Industries, Inc. Marine in bilge blower
DE10053361C1 (en) * 2000-10-27 2002-06-06 Mtu Aero Engines Gmbh Blade grid arrangement for turbomachinery
FR2824597B1 (en) * 2001-05-11 2004-04-02 Snecma Moteurs REDUCTION OF VIBRATION IN A STRUCTURE COMPRISING A ROTOR AND FIXED DISTURBANCE SOURCES
FR2890569B1 (en) * 2005-09-09 2007-11-16 Groupe Leader Sa Sa FAN FOR FIRE FIGHTING INCLUDING AIR FLOW RECTIFIER
JP4678406B2 (en) * 2005-11-29 2011-04-27 株式会社Ｉｈｉ Stator blade row of turbo fluid machine
WO2014058478A1 (en) 2012-10-09 2014-04-17 United Technologies Corporation Geared low fan pressure ratio fan exit guide vane stagger angle
DE102016007205A1 (en) * 2016-06-08 2017-12-14 Ziehl-Abegg Se fan unit
US11002141B2 (en) * 2017-05-22 2021-05-11 General Electric Company Method and system for leading edge auxiliary turbine vanes
US10883515B2 (en) 2017-05-22 2021-01-05 General Electric Company Method and system for leading edge auxiliary vanes
JP2022096823A (en) * 2020-12-18 2022-06-30 日本電産株式会社 Series axial flow fan

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4720239A (en) * 1982-10-22 1988-01-19 Owczarek Jerzy A Stator blades of turbomachines
WO1989012174A1 (en) * 1988-06-08 1989-12-14 ABB Fläkt AB Guide vane for an axial fan
US4981414A (en) * 1988-05-27 1991-01-01 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US821347A (en) * 1904-04-21 1906-05-22 Jens William Ogidius Elling Fractional-supply steam and gas turbine.
US2839239A (en) * 1954-06-02 1958-06-17 Edward A Stalker Supersonic axial flow compressors
FR1200484A (en) * 1958-06-26 1959-12-22 Alsthom Cgee Water drainage device in steam turbines
US3883264A (en) * 1971-04-08 1975-05-13 Gadicherla V R Rao Quiet fan with non-radial elements
US3747343A (en) * 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
US5152661A (en) * 1988-05-27 1992-10-06 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer
US5246339A (en) * 1988-06-08 1993-09-21 Abb Flakt Ab Guide vane for an axial fan

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4720239A (en) * 1982-10-22 1988-01-19 Owczarek Jerzy A Stator blades of turbomachines
US4981414A (en) * 1988-05-27 1991-01-01 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer
WO1989012174A1 (en) * 1988-06-08 1989-12-14 ABB Fläkt AB Guide vane for an axial fan

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
1988 International Conference on Noise Control Engineering, inter-noise 88, Avignon, France, 30 August - 1 September 1988, Fan Noise-Generation Mechanisms and Control Methods (sid 767 - sid 776 (W. NEISE), see page 771, 3rd paragraph. *
The Journal of the Acoustical Society of America 51 (1972):5, part 1, Research on Fan Noise Generation (page 1427 - page 1438) (M.J. BENZAKEIN). *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6803042B2 (en) 1993-10-29 2004-10-12 U.S. Army Medical Research Materiel Command Oral or intranasal vaccines using hydrophobic complexes having proteosomes and lipopolysaccharides
GB2401654A (en) * 2003-05-14 2004-11-17 Rolls Royce Plc A stator vane assembly for a turbomachine
GB2401654B (en) * 2003-05-14 2006-04-19 Rolls Royce Plc A stator vane assembly for a turbomachine
GB2420157A (en) * 2003-05-14 2006-05-17 Rolls Royce Plc Stator vane assembly with non-uniform blade spacing
GB2420157B (en) * 2003-05-14 2006-06-28 Rolls Royce Plc A stator vane assembly for a turbomachine
DE102010002395A1 (en) * 2010-02-26 2011-09-01 Rolls-Royce Deutschland Ltd & Co Kg Turbofan engine comprises support strut which is provided as aerodynamically formed structural guide vanes opposite to aerodynamic guide vanes of larger blade thickness
DE102010002395B4 (en) * 2010-02-26 2017-10-19 Rolls-Royce Deutschland Ltd & Co Kg Turbofan engine with guide vanes and support struts arranged in the bypass duct

Also Published As

Publication number Publication date
RU2101576C1 (en) 1998-01-10
KR100229693B1 (en) 1999-11-15
EP0680563A1 (en) 1995-11-08
SE9102150L (en) 1993-01-10
DE69224853T2 (en) 1998-08-20
DK0680563T3 (en) 1998-10-07
US5470200A (en) 1995-11-28
FI102310B (en) 1998-11-13
CA2111103A1 (en) 1993-01-21
FI940057A0 (en) 1994-01-07
AU657353B2 (en) 1995-03-09
SE9102150D0 (en) 1991-07-09
ES2113951T3 (en) 1998-05-16
FI940057L (en) 1994-01-07
AU2331292A (en) 1993-02-11
SE500471C2 (en) 1994-07-04
JPH06509150A (en) 1994-10-13
EP0680563B1 (en) 1998-03-18
FI102310B1 (en) 1998-11-13
DE69224853D1 (en) 1998-04-23

Similar Documents

Publication Publication Date Title
EP0680563A1 (en) Guide vane means
KR970001834B1 (en) Impeller for transverse fan
Neise Noise reduction in centrifugal fans: a literature survey
US3937590A (en) Acoustic duct with peripherally segmented acoustic treatment
CA1223577A (en) Axial flow fan
EP0350427B1 (en) Variable flow radial compressor inlet flow fences
Kameier et al. Rotating blade flow instability as a source of noise in axial turbomachines
Neise Review of noise reduction methods for centrifugal fans
EP0715066A3 (en) Fan assembly
US6375416B1 (en) Technique for reducing acoustic radiation in turbomachinery
US5388956A (en) Fan assembly and method for reducing fan noise
US5709529A (en) Optimization of turbomachinery harmonics
WO2002052109A1 (en) Acoustic liner and a fluid pressurizing device and method utilizing same
CA2127588A1 (en) Rotary throat cutoff device and method for reducing centrifugal fan noise
JPH0814193A (en) Impeller for horizontal type fan
JPH0319366B2 (en)
US4232994A (en) Centrifugal turbomachine
US8777560B2 (en) Method and apparatus for controlling tonal noise from subsonic fans
GB2187876A (en) Toroidal whistle
RU195929U1 (en) CENTRIFUGAL FAN OPERATING WHEEL
Krishnappa Effect of modulated blade spacing on centrifugal fan noise
US4997343A (en) Gas-dynamic pressure-wave machine with reduced noise amplitude
SCHARPF An experimental investigation of the sources of propeller noise due to turbulence ingestion(Ph. D. Thesis)
Suzuki et al. Study on the reduction of rotating noise emitted from centrifugal fan
Suzuki et al. Infrasound in partial discharge from axial fans and its control

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AT AU BB BG BR CA CH CS DE DK ES FI GB HU JP KP KR LK LU MG MN MW NL NO PL RO RU SD SE US

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE CH DE DK ES FR GB GR IT LU MC NL SE BF BJ CF CG CI CM GA GN ML MR SN TD TG

DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
EX32 Extension under rule 32 effected after completion of technical preparation for international publication
LE32 Later election for international application filed prior to expiration of 19th month from priority date or according to rule 32.2 (b)
WWE Wipo information: entry into national phase

Ref document number: 2111103

Country of ref document: CA

WWE Wipo information: entry into national phase

Ref document number: 1992915625

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 940057

Country of ref document: FI

WWE Wipo information: entry into national phase

Ref document number: 08175356

Country of ref document: US

REG Reference to national code

Ref country code: DE

Ref legal event code: 8642

WWP Wipo information: published in national office

Ref document number: 1992915625

Country of ref document: EP

WWG Wipo information: grant in national office

Ref document number: 1992915625

Country of ref document: EP

WWG Wipo information: grant in national office

Ref document number: 940057

Country of ref document: FI