EP1788255A1 - Roue de compresseur radial - Google Patents

Roue de compresseur radial Download PDF

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Publication number
EP1788255A1
EP1788255A1 EP05025048A EP05025048A EP1788255A1 EP 1788255 A1 EP1788255 A1 EP 1788255A1 EP 05025048 A EP05025048 A EP 05025048A EP 05025048 A EP05025048 A EP 05025048A EP 1788255 A1 EP1788255 A1 EP 1788255A1
Authority
EP
European Patent Office
Prior art keywords
curved
blades
edge
compressor impeller
radial compressor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP05025048A
Other languages
German (de)
English (en)
Inventor
Lars Schlüter
Theodor Dr. Wallmann
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.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP05025048A priority Critical patent/EP1788255A1/fr
Priority to PCT/EP2006/067919 priority patent/WO2007057292A1/fr
Priority to CN200680042871.3A priority patent/CN101310112B/zh
Priority to EP06807648A priority patent/EP1948939B1/fr
Priority to ES06807648T priority patent/ES2336371T3/es
Priority to DE502006005551T priority patent/DE502006005551D1/de
Priority to US12/084,920 priority patent/US8277187B2/en
Priority to AT06807648T priority patent/ATE450712T1/de
Publication of EP1788255A1 publication Critical patent/EP1788255A1/fr
Priority to NO20082659A priority patent/NO338811B1/no
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a radial compressor impeller, comprising a wheel disc and evenly arranged in the circumferential direction blades with an inlet edge and a trailing edge.
  • Radial compressors convert mechanical energy into pressure energy by exploiting centrifugal acceleration.
  • Radial compressors consist essentially of an impeller which is mounted on a driving shaft, a diffuser and a housing.
  • the impeller has a plurality of curved blades.
  • the mechanical design of the impeller takes place in the manner of a closed or semi-open impeller.
  • the blades With closed impellers, the blades are provided with a cover disk, with half-open wheels, the blades have a free outer edge.
  • the conveying gas is sucked in axially approximately in the center of the compressor and compressed by the centrifugal force, supported also by the curved shape of the blades, and accelerated to the outside.
  • the kinetic energy is largely converted into additional pressure and the delivery gas is further compressed.
  • centrifugal compressors have a curved characteristic.
  • a stable characteristic is sought, which is characterized by an increasing delivery pressure at a decreasing flow rate.
  • the operating range of a centrifugal compressor is limited by the so-called pump limit. This is generally the point of the characteristic with the smallest flow. Beyond the surge line, the centrifugal compressor no longer be used, because the flow dissolves from the blades and a stable operation is no longer guaranteed.
  • centrifugal compressor impeller according to the preamble is known.
  • the blades of this impeller are provided with through holes through which the conveying gas is supplied from a convex blade pressure side to a concave blade suction side, so that the vortices formed on the blade suction side at low flow rates and high pressure ratios, are transported away.
  • the invention has for its object to provide a centrifugal compressor impeller, which allows an increased stable operating range with high efficiency. Furthermore, the invention has for its object to provide a manufacturing method for such a centrifugal compressor impeller.
  • the first object is achieved by a radial compressor impeller consisting of a wheel disc and uniformly arranged in the circumferential direction blades.
  • the blades have an entry edge and an exit edge, wherein at least a portion of the surface of the blades is a double curved portion, the generatrix of which is formed as a curved line, and the curved portion perpendicular to the generatrix is also curved.
  • the surface in the curved portion is formed double-curved, ie, starting from a point on the surface of the curved portion, the surface extends in two surface-spanning directions curved. All lines passing through this point are therefore curved and not formed as a straight line.
  • the curved section is characterized overall by the fact that all lines - including the generatrix - are curved on the surface in this subarea. This area thus forms a so-called sculptured surface.
  • generatrix is understood to mean a line which is part of the surface in a direction spanning the surface (for example the x direction), that is to say has the course of the surface in this direction and defines it.
  • the surface is formed and defined by movement or displacement of the generatrices in a second direction, not parallel to the generatrix (for example y-direction, perpendicular to the x-direction).
  • the generator does not necessarily have to be static, but it can change in dependence on the position of the generators in the second direction.
  • the advantage of the invention is to be seen in particular in that a double-curved surface is better adapted to the three-dimensional development of the flow and thus results in an improved flow behavior.
  • the stable flow behavior in turn leads to the stabilization of the compressor characteristic and to increase the efficiency of the centrifugal compressor.
  • blade surfaces of centrifugal compressor impellers are nowadays often defined by means of rectilinear generators.
  • rule surfaces ruled surfaces
  • rule surface lines For the production of these surfaces is usually resorted to a machining in flank milling process (flank milling) by means of cylindrical or conical roller mill. In this case, the milling cutter is brought into engagement so that its ideal surface line in the cutting area is oriented parallel to the respective straight line straight line of the blade surface.
  • a further subregion of the surface of the blades is designed as a ruled-surface subregion whose generatrix is a straight line.
  • This subarea thus forms a ruled surface, so that at least one straight line runs through each point of this subarea.
  • transition from the double-curved to the ruled-surface partial area is preferably continuous. So there are no kinks or edges between these two parts. The transition between these two subareas is rounded. This ensures that no turbulence is generated by separation of the flow due to surface irregularities.
  • the vanes have a hub edge and an approximately opposite outer edge, wherein the double-curved portion adjacent to the outer edge and the ruled surface portion of the hub edge.
  • the hub edge is adjacent to a hub of the wheel disc edge, so it is located in the lower part of the blade.
  • the outer edge is approximately opposite the hub edge. It is designed as a free edge on half-open wheels. With closed wheels it adjoins the cover disc.
  • the outer edge, hub edge, leading edge and trailing edge define the blade, wherein the outer edge and the hub edge each connect the leading edge to the trailing edge.
  • the double curved portion and / or the ruled portion extends from the leading edge to the trailing edge.
  • the double-curved partial area and the regular-area partial area are approximately the same size.
  • the surface of the blades has a plurality of double curved portions.
  • the surface is composed of a plurality of double-curved and ruled-surface portions that are alternately arranged, thereby improving the aerodynamic properties of the blade.
  • a further advantageous embodiment is achieved in that, adjacent to the hub edge and to the outer edge, a double-curved partial region is provided, between which a ruled-surface partial region is arranged.
  • An efficient deflection of the flow with reduced risk of tearing is achieved according to a particularly preferred embodiment in that the entire surface of the blades is doubly curved, that is completely formed by a curved generatrix.
  • the blades are preferably designed such that the curvature of the generatrix changes from the leading edge toward the trailing edge. This means that the generatrix of the double-curved section which extends in the transverse direction of the blades has a curvature which varies in the longitudinal direction of the blade.
  • the wheel disc, the blades and possibly the cover disc form separate units.
  • the individual elements of the impeller can be manufactured separately and joined together later, so that a high number of degrees of freedom, in particular for the design of the blades is ensured.
  • the object is further achieved by a method for producing a centrifugal compressor impeller, which consists of a wheel disc and evenly in the circumferential direction arranged blades, wherein the surface of the blades is at least partially made by point milling by means of a Kugelkopf- or radius cutter.
  • a manufacturing process is not applicable in which the cutter contacts the blade surface linearly, as is the case, for example, with the usual use of a roll mill.
  • the design of the double curved sections requires a selective contact of the cutter with the blade surface, which ensures additional degrees of freedom in the manufacture of the blades. This point contact occurs during face milling. Accordingly, a high number of milling paths is provided in order to achieve a sufficiently high surface quality. By face milling, in particular the entire blade surface, even in the ruled area sub-area, can be designed.
  • FIG. 1 a single-flow (conveying gas supply only from one side) and single-stage working radial compressor 2 is shown.
  • the centrifugal compressor 2 comprises an impeller 4, a rotatable in the direction of rotation D shaft 6, on which the impeller 4 is mounted and which defines an axial direction A and a diffuser 8 and a cover plate 10.
  • the impeller 4 consists of a wheel disc 12 and a plurality of over the circumference arranged blades 14.
  • a conveying gas is sucked in axially in the region of the shaft 6 and accelerated radially outwardly via the channels formed between the blades by the centrifugal force. This is indicated by the arrows F, which indicate the flow direction of the conveying gas.
  • both the speed and the pressure of the delivery gas increases.
  • the flow is slowed down, resulting in a further increase in the pressure of the delivery gas.
  • the conveying gas leaves the centrifugal compressor again in the axial direction.
  • the aerodynamic geometry of the blades 14 contributes to the correct energy conversion.
  • This geometry is shown for example in FIG 2a and 2b, which show a side view and a plan view of a first embodiment of the blades 14.
  • the blade 14 has an entry edge 16. At the other end in the longitudinal direction of the blade 14 is an exit edge 18, which is oriented in the mounted state to the diffuser 8.
  • the blade 14 In a closed impeller 2, the blade 14 is provided with the cover plate 10, in a semi-open impeller, the blade 14 has a free trailing edge 18.
  • a hub edge 20 of the blade 14 extends over the surface of the wheel disc 12 and abuts directly on this in a hub region.
  • the blade 14 has an outer edge 22.
  • the generatrix 24 of the vane surface leading with respect to the direction of rotation D is convexly curved.
  • the surface of the blades 14 is defined by a respective generatrix 24. This extends in the transverse direction of the blade 14, i. From the hub edge 20 to the outer edge 22. In the longitudinal direction of the blade 14, ie in the direction of the leading edge 16 to the trailing edge 18, the generator 24 changes. Viewed differently, the entire surface is composed of a plurality of infinitesimal sub-surfaces, each are defined by different static generators.
  • the surface is divided into a double-curved portion 26 and a ruled-surface portions 28.
  • the double curved portion 26 abuts the outer edge 22 and extends longitudinally from the leading edge 16 to the trailing edge 18.
  • the ruled portion 28 abuts the hub edge 20 and also extends like the double curved portion 26 along the entire blade 14. Die two sections 26, 28 form a continuous transition between them, so that the surface of the blade 14 has no edges, grooves or protrusions, which could have a negative influence on the development of the flow.
  • the generator 24 is also subdivided into a curved region 24a and a control surface region 24b, which merge smoothly into one another.
  • the shape of the blade 14 is adapted to the flow requirements with regard to the stabilization of the flow.
  • the complex geometry of the blades 14 requires a manufacturing method that ensures degrees of freedom in all three spatial directions in making the double curved portion 26.
  • Particularly suitable in this case is the use of a face milling cutter, which can produce curved planes with different directions of curvature and radii of curvature through the point contact with the surface of the blade 14.
  • FIG. 3a and FIG. 3b A further embodiment of the blade 14 is shown in FIG. 3a and FIG. 3b.
  • the blade 14 has for its entire surface a curved generatrix 24a which extends from the leading edge 16 to the trailing edge 18 and is oriented concavely to the flow direction F of the conveying gas. It can also be seen from FIGS. 3 a and 3 b that the curvature profile of the generatrix 24 a changes in the flow direction F from the inlet edge 16 to the outlet edge 28. In the side view in FIG. 3 a, the blade has a convexly curved leading edge 16.
  • the generatrix 24 of the blade surface leading in relation to the direction of rotation D is concavely curved.
  • a double-curved partial region 26 and a ruled-surface partial region 28 are provided here.
  • the double curved portion 26 in this case forms about 1/3 of the entire surface.
  • a further preferred embodiment of the blades 14 is illustrated, namely a in the side view in FIG 4a is a concave curved edge 16, which improves the aerodynamic properties of the blade 14.
  • the blade 14 has two double-curved portions 26 which adjoin the hub edge 20 and the outer edge 22 and between which a ruled-surface portion 28 is arranged. This is shown in FIG. 5a and FIG. 5b. Here, the leading edge 16 is formed curved again. The individual subregions 26, 28 are approximately the same size.
  • the exemplary embodiment according to FIGS. 6a and 6b is essentially a combination of the exemplary embodiments according to FIGS. 4a, 4b and FIGS. 5a, 5b.
  • the generator 24 is composed of two oppositely curved regions 24a, which are connected to one another via a control surface region 24b. Therefore, there are also two edge-side, double-curved partial regions 26 as well as a ruled-surface partial region 28 arranged therebetween.
  • the double-curved partial area 26 illustrated in the figures covers in each case a large surface area of the blade surface of-depending on the exemplary embodiment-20% to 60% of the total surface area. Only in the exemplary embodiment according to FIGS. 3a, 3b does the curved partial region 26 form 100% or nearly 100% of the total surface.
  • the partial regions 26, 28 are only roughly indicated in the figures by the dashed line. Since the curvature changes in the longitudinal direction of the blade 14, there is the possibility that within the illustrated subregions 26 in limited sections, the generatrix is not curved but is a line. This may occur, for example, when the curvature within a portion 26 is changed from convex to concave.
  • the operating behavior of the radial compressor 2 for a certain speed is described qualitatively with reference to the diagram in FIG. 7 by a compressor characteristic curve VK.
  • VK the pressure ratio p P 0 represented by the flow rate V ⁇ , where p is the discharge pressure at the outlet of the compressor 2 and P 0, the intake pressure at the leading edge 16.
  • the characteristic VK is limited on the left side by the surge limit S. There, the flow dissolves at too small flow rates and high pressure ratios of the blades 14.
  • the point on the characteristic curve VK in which this happens is the tear-off point W.
  • the operating point B of the radial compressor 2 is the point of intersection of the compressor characteristic curve VK with a system characteristic curve AK. As a rule, B moves on the compressor characteristic curve VK depending on the system parameters.
  • the compressor characteristic VK 'and the associated tear-off point W' and surge limit S 'of a conventional centrifugal compressor are indicated. Thanks to the improved aerodynamics of the blades 14, the slope of the characteristic curve VK in the direction of the surge limit is steeper. As a result, the operating point B is at higher pressure ratios than the operating point B 'of a conventional centrifugal compressor, when the two compressors deliver about the same amount of conveying gas, so that a higher efficiency of the centrifugal compressor 2 is achieved.
  • a further improvement of the compressor characteristics is the displacement of the tear-off point W to lower volume flows V ⁇ than the tear-off point W 'of a conventional centrifugal compressor.
  • the flow behavior of the delivery gas is stabilized and the centrifugal compressor 2 works at low flow rates V ⁇ still flawless and safe.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Compressors, Vaccum Pumps And Other Relevant Systems (AREA)
  • Supercharger (AREA)
EP05025048A 2005-11-16 2005-11-16 Roue de compresseur radial Withdrawn EP1788255A1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP05025048A EP1788255A1 (fr) 2005-11-16 2005-11-16 Roue de compresseur radial
PCT/EP2006/067919 WO2007057292A1 (fr) 2005-11-16 2006-10-30 Roue mobile de compresseur radial
CN200680042871.3A CN101310112B (zh) 2005-11-16 2006-10-30 离心式压缩机叶轮
EP06807648A EP1948939B1 (fr) 2005-11-16 2006-10-30 Roue mobile de compresseur radial
ES06807648T ES2336371T3 (es) 2005-11-16 2006-10-30 Rodote con alabes para compresor centrifugo.
DE502006005551T DE502006005551D1 (de) 2005-11-16 2006-10-30 Radialverdichter-laufrad
US12/084,920 US8277187B2 (en) 2005-11-16 2006-10-30 Radial compressor rotor
AT06807648T ATE450712T1 (de) 2005-11-16 2006-10-30 Radialverdichter-laufrad
NO20082659A NO338811B1 (no) 2005-11-16 2008-06-13 Radialkompressor-rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05025048A EP1788255A1 (fr) 2005-11-16 2005-11-16 Roue de compresseur radial

Publications (1)

Publication Number Publication Date
EP1788255A1 true EP1788255A1 (fr) 2007-05-23

Family

ID=36087765

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05025048A Withdrawn EP1788255A1 (fr) 2005-11-16 2005-11-16 Roue de compresseur radial
EP06807648A Not-in-force EP1948939B1 (fr) 2005-11-16 2006-10-30 Roue mobile de compresseur radial

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP06807648A Not-in-force EP1948939B1 (fr) 2005-11-16 2006-10-30 Roue mobile de compresseur radial

Country Status (8)

Country Link
US (1) US8277187B2 (fr)
EP (2) EP1788255A1 (fr)
CN (1) CN101310112B (fr)
AT (1) ATE450712T1 (fr)
DE (1) DE502006005551D1 (fr)
ES (1) ES2336371T3 (fr)
NO (1) NO338811B1 (fr)
WO (1) WO2007057292A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2918849A4 (fr) * 2012-12-13 2015-11-25 Mitsubishi Heavy Ind Ltd Compresseur
WO2015189234A1 (fr) * 2014-06-12 2015-12-17 Abb Turbo Systems Ag Compresseur permettant d'obtenir un débit de dimensionnement élevé

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US8529210B2 (en) 2010-12-21 2013-09-10 Hamilton Sundstrand Corporation Air cycle machine compressor rotor
US9102397B2 (en) 2011-12-20 2015-08-11 General Electric Company Airfoils including tip profile for noise reduction and method for fabricating same
CN103256248B (zh) * 2012-02-21 2015-08-26 珠海格力电器股份有限公司 叶轮及包括该叶轮的离心压缩机
ITCO20130024A1 (it) * 2013-06-13 2014-12-14 Nuovo Pignone Srl Giranti di compressore
WO2015002066A1 (fr) * 2013-07-04 2015-01-08 株式会社Ihi Rouet de compresseur, compresseur centrifuge, procédé d'usinage pour rouet de compresseur et appareil d'usinage pour rouet de compresseur
US10151321B2 (en) 2013-10-16 2018-12-11 United Technologies Corporation Auxiliary power unit impeller blade
CN106164496A (zh) * 2014-01-07 2016-11-23 诺沃皮尼奥内股份有限公司 具有非线性叶片前缘的离心压缩机叶轮及相关联的设计方法
DE102014219058A1 (de) * 2014-09-22 2016-03-24 Siemens Aktiengesellschaft Radialverdichterlaufrad und zugehöriger Radialverdichter
CN106351872A (zh) * 2016-09-12 2017-01-25 深圳友铂科技有限公司 一种兼顾气动与强度的压气机转子叶片
US10605087B2 (en) * 2017-12-14 2020-03-31 United Technologies Corporation CMC component with flowpath surface ribs
FR3089576B1 (fr) * 2018-12-05 2022-11-25 Safran Helicopter Engines Rouet centrifuge
KR20200124375A (ko) * 2019-04-23 2020-11-03 현대자동차주식회사 터보차저 컴프레서휠
CN110657126B (zh) * 2019-09-10 2021-07-30 中国科学院工程热物理研究所 控制离心叶轮流动的非轴对称轮毂结构、离心叶轮
JP7386333B2 (ja) * 2020-04-23 2023-11-24 三菱重工マリンマシナリ株式会社 インペラ、及び遠心圧縮機
US11506059B2 (en) * 2020-08-07 2022-11-22 Honeywell International Inc. Compressor impeller with partially swept leading edge surface
CN112922899A (zh) * 2021-02-05 2021-06-08 深圳森蓝忠信科技有限公司 一种轴流式压气机转子叶片
CN113738695B (zh) * 2021-08-25 2024-05-10 哈尔滨工业大学 一种具有抛物线型前缘叶片的高性能呼吸机离心叶轮
DE102022203619A1 (de) 2022-04-11 2023-10-12 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verdichterschaufel zur Umlenkung eines strömenden Mediums in einem Verdichter, insbesondere Radialverdichter, Rotor und System
DE102022127147B4 (de) 2022-10-17 2024-06-27 Man Energy Solutions Se Verdichter und Turbolader

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DE897470C (de) * 1944-01-27 1953-12-14 Sulzer Ag Laeufer fuer Schleuderverdichter mit diagonalem Stroemungsverlauf
DE4214753A1 (de) 1992-05-04 1993-11-11 Asea Brown Boveri Radialverdichter-Laufrad
US6588485B1 (en) * 2002-05-10 2003-07-08 Borgwarner, Inc. Hybrid method for manufacturing titanium compressor wheel
WO2005090794A1 (fr) * 2004-03-23 2005-09-29 Mitsubishi Heavy Industries, Ltd. Compresseur centrifuge et procédé de fabrication d'une roue de compresseur

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EP0775248B1 (fr) * 1994-06-10 1999-09-15 Ebara Corporation Turbomachines centrifuges ou a circulation mixte
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Publication number Priority date Publication date Assignee Title
DE897470C (de) * 1944-01-27 1953-12-14 Sulzer Ag Laeufer fuer Schleuderverdichter mit diagonalem Stroemungsverlauf
DE4214753A1 (de) 1992-05-04 1993-11-11 Asea Brown Boveri Radialverdichter-Laufrad
US6588485B1 (en) * 2002-05-10 2003-07-08 Borgwarner, Inc. Hybrid method for manufacturing titanium compressor wheel
WO2005090794A1 (fr) * 2004-03-23 2005-09-29 Mitsubishi Heavy Industries, Ltd. Compresseur centrifuge et procédé de fabrication d'une roue de compresseur
US20050260074A1 (en) * 2004-03-23 2005-11-24 Mitsubishi Heavy Industries, Ltd Centrifugal compressor and manufacturing method for impeller

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2918849A4 (fr) * 2012-12-13 2015-11-25 Mitsubishi Heavy Ind Ltd Compresseur
WO2015189234A1 (fr) * 2014-06-12 2015-12-17 Abb Turbo Systems Ag Compresseur permettant d'obtenir un débit de dimensionnement élevé

Also Published As

Publication number Publication date
US20090220346A1 (en) 2009-09-03
NO338811B1 (no) 2016-10-24
DE502006005551D1 (de) 2010-01-14
CN101310112B (zh) 2011-04-13
ES2336371T3 (es) 2010-04-12
ATE450712T1 (de) 2009-12-15
EP1948939A1 (fr) 2008-07-30
NO20082659L (no) 2008-08-08
US8277187B2 (en) 2012-10-02
WO2007057292A1 (fr) 2007-05-24
CN101310112A (zh) 2008-11-19
EP1948939B1 (fr) 2009-12-02

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