EP1948939B1 - Roue mobile de compresseur radial - Google Patents

Roue mobile de compresseur radial Download PDF

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Publication number
EP1948939B1
EP1948939B1 EP06807648A EP06807648A EP1948939B1 EP 1948939 B1 EP1948939 B1 EP 1948939B1 EP 06807648 A EP06807648 A EP 06807648A EP 06807648 A EP06807648 A EP 06807648A EP 1948939 B1 EP1948939 B1 EP 1948939B1
Authority
EP
European Patent Office
Prior art keywords
curved
blades
ruled
section
generatix
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.)
Not-in-force
Application number
EP06807648A
Other languages
German (de)
English (en)
Other versions
EP1948939A1 (fr
Inventor
Lars Schlüter
Theodor 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 EP06807648A priority Critical patent/EP1948939B1/fr
Publication of EP1948939A1 publication Critical patent/EP1948939A1/fr
Application granted granted Critical
Publication of EP1948939B1 publication Critical patent/EP1948939B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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 uniformly circumferentially arranged blades with an inlet edge and a trailing 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 is also curved perpendicular to the generatrix.
  • the invention relates to a method for producing a radial compressor impeller of this type.
  • 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 Kenn aspired to line 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 according to claim 1 solved.
  • the back-related claims contain advantageous developments of the invention.
  • 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 Overall, the area is characterized by the fact that all the 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, 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 blades 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 according to claim 13. arranged arranged blades, wherein the surface of the blades is at least partially made by point milling by means of a ball or radius cutter. Because of the geometrical features of the blades, 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 is a single-flow (conveying gas supply only from one side) and single-stage radial compressor 2 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 for example in 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 from 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 Another embodiment of the blade 14 is shown in FIG. 3a and FIG. 3b shown.
  • 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. From the FIGS. 3a and 3b It can also be seen that the curvature of the generatrix 24a changes in the flow direction F from the leading edge 16 to the trailing edge 28. In the side view in FIG. 3a the blade has a convexly curved leading edge 16.
  • the generatrix 24 of the vane surface leading with respect to the direction of rotation D is concavely curved.
  • a double curved portion 26 and a ruled portion 28 are provided.
  • the double curved portion 26 in this case forms about 1/3 of the entire surface.
  • FIGS. 4a, 4b is a further preferred embodiment of the blades 14 illustrates, namely a in the side view in FIG. 4a Concavely curved leading 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 in FIG 5a and FIG 5b shown. Here, the leading edge 16 is formed curved again. The individual subregions 26, 28 are approximately the same size.
  • the embodiment according to the 6a and 6b is essentially a combination of the embodiments according to the FIGS. 4a, 4b and FIGS. 5a, 5b ,
  • the generator 24 is composed of two oppositely curved portions 24a, which are connected to each other via a control surface area 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 embodiment according to FIG. 3a, 3b the curved portion 26 forms 100% or nearly 100% of the total surface area.
  • 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 qualitatively based on the diagram in FIG. 7 described by a compressor characteristic VK.
  • a compressor characteristic VK In this diagram is the pressure ratio p P 0 over the volume flow where p is the delivery pressure at the exit of the compressor 2 and P 0 is the intake pressure at the entry 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 break point W to lower volume flows V than the break point W 'of a conventional radial compressor. Thus, the flow behavior of the delivery gas is stabilized and the centrifugal compressor 2 still works properly and safely at low flow rates V.

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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)

Claims (13)

  1. Roue ( 4 ) de compresseur radial,
    constituée d'un flasque ( 12 ) de roue et d'aubes ( 14 ) réparties uniformément dans la direction périphérique et ayant un bord ( 16 ) d'entrée, un bord ( 18 ) de sortie, au moins une zone partielle de la surface des aubes ( 14 ) étant une zone ( 26 ) partielle à courbure double, dont la génératrice ( 24a ) est sous la forme d'une ligne courbée et la zone ( 26 ) partielle courbée est courbée également perpendiculairement à la génératrice ( 24a ),
    caractérisée en ce que
    la génératrice ( 24 ) est subdivisée en une zone ( 24a ) courbée en une zone ( 24b ) à surface régulière, la génératrice de la zone partielle à surface régulière étant une ligne droite,
    dans laquelle la génératrice de la zone ( 24b ) à surface régulière se transforme d'une manière continue en la zone ( 24a ) courbée.
  2. Roue ( 4 ) de compresseur radial suivant la revendication 1,
    caractérisée en ce que
    une autre zone partielle de la surface des aubes ( 14 ) est constituée sous la forme d'une zone (28 ) partielle à surface régulière, dont la génératrice ( 24b ) est sous la forme d'une ligne droite.
  3. Roue ( 4 ) de compresseur radial suivant la revendication 2,
    caractérisée en ce que
    la transition de la zone ( 26 ) partielle à courbure double à la zone ( 26, 28 ) partielle à surface régulière est continue.
  4. Roue ( 4 ) de compresseur radial suivant la revendication 2 ou 3,
    caractérisée en ce que
    les aubes ( 14 ) ont un bord ( 20 ) de moyeu et un bord ( 22 ) extérieur à peu près opposé, la zone ( 26 ) partielle à courbure double étant voisine du bord ( 22 ) extérieur et la zone ( 28 ) partielle à surface régulière du bord ( 20 ) de moyeu.
  5. Roue ( 4 ) de compresseur radial suivant l'une des revendications 2 à 4,
    caractérisée en ce que
    la zone ( 26 ) partielle à courbure double et/ou la zone ( 28 ) partielle à surface régulière s'étendent du bord ( 16 ) d'entrée au bord ( 48 ) de sortie.
  6. Roue ( 4 ) de compresseur radial suivant l'une des revendications 2 à 5,
    caractérisée en ce que
    la zone ( 26 ) partielle à courbure double et la zone ( 28 ) partielle à surface régulière sont à peu près de même grandeur.
  7. Roue ( 4 ) de compresseur radial suivant l'une des revendications 2 à 6,
    caractérisée en ce que
    la surface des aubes ( 14 ) à plusieurs zones ( 26 ) partielles à courbure double séparées les unes des autres par une zone ( 28 ) partielle à surface régulière.
  8. Roue ( 4 ) de compresseur radial suivant la revendication 7,
    caractérisée en ce que
    au voisine du bord ( 20 ) de moyeu et du bord ( 22 ) extérieur sont prévues deux zones ( 26 ) partielles à courbure double, entre lesquelles est disposée une zone ( 28 ) partielle à surface régulière.
  9. Roue ( 4 ) de compresseur radial suivant l'une des revendications précédentes,
    caractérisée en ce que
    toute la surface des aubes ( 14 ) est courbée et a une ligne courbée comme génératrice ( 24a ).
  10. Roue ( 4 ) de compresseur radial suivant l'une des revendications précédentes,
    caractérisée en ce que
    le bord ( 16 ) d'entrée est courbée.
  11. Roue ( 4 ) de compresseur radial suivant l'une des revendications précédentes,
    caractérisée en ce que
    le tracé de courbure de la génératrice ( 24 ) se modifie du bord ( 16 ) d'entrée en direction du bord ( 18 ) de sortie.
  12. Roue ( 4 ) de compresseur radial suivant l'une des revendications précédentes,
    caractérisée en ce que le moyeu ( 12 ) de la roue, les aubes ( 14 ) et/ou un flasque de couverture forme des unités séparées.
  13. Procédé de fabrication d'une roue ( 4 ) de compresseur radial,
    qui est constituée d'un flasque ( 12 ) de roue et d'aubes ( 14 ) réparties uniformément dans la direction périphérique,
    caractérisé en ce que
    on fabrique la surface des aubes ( 14 ) au moins par partie par fraisage en bout,
    au moins une zone partielle de la surface des aubes ( 14 ) est une zone ( 26 ) partielle courbée, dont la génératrice ( 24a ) sous la forme d'une ligne courbée, et
    la zone ( 26 ) partielle courbée est courbée également perpendiculairement à la génératrice ( 24a ),
    la génératrice ( 24 ) étant subdivisée en une zone ( 24a ) courbée en une zone ( 24b ) à surface régulière,
    dans lequel la génératrice de la zone partielle à surface régulière est une ligne droite,
    dans lequel la génératrice de la surface ( 24b ) régulière se transforme en continue en la zone ( 24a ) courbée.
EP06807648A 2005-11-16 2006-10-30 Roue mobile de compresseur radial Not-in-force EP1948939B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06807648A EP1948939B1 (fr) 2005-11-16 2006-10-30 Roue mobile de compresseur radial

Applications Claiming Priority (3)

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
EP06807648A EP1948939B1 (fr) 2005-11-16 2006-10-30 Roue mobile de compresseur radial

Publications (2)

Publication Number Publication Date
EP1948939A1 EP1948939A1 (fr) 2008-07-30
EP1948939B1 true EP1948939B1 (fr) 2009-12-02

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 Before (1)

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

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022127147A1 (de) 2022-10-17 2024-04-18 Man Energy Solutions Se Verdichter und Turbolader
DE102022127147B4 (de) 2022-10-17 2024-06-27 Man Energy Solutions Se Verdichter und Turbolader

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WO2007057292A1 (fr) 2007-05-24
US20090220346A1 (en) 2009-09-03
ES2336371T3 (es) 2010-04-12
CN101310112B (zh) 2011-04-13
DE502006005551D1 (de) 2010-01-14
CN101310112A (zh) 2008-11-19
ATE450712T1 (de) 2009-12-15
EP1948939A1 (fr) 2008-07-30
EP1788255A1 (fr) 2007-05-23
US8277187B2 (en) 2012-10-02
NO338811B1 (no) 2016-10-24
NO20082659L (no) 2008-08-08

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