WO2015189234A1 - Compresseur permettant d'obtenir un débit de dimensionnement élevé - Google Patents

Compresseur permettant d'obtenir un débit de dimensionnement élevé Download PDF

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Publication number
WO2015189234A1
WO2015189234A1 PCT/EP2015/062877 EP2015062877W WO2015189234A1 WO 2015189234 A1 WO2015189234 A1 WO 2015189234A1 EP 2015062877 W EP2015062877 W EP 2015062877W WO 2015189234 A1 WO2015189234 A1 WO 2015189234A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
sectional area
blades
narrowest cross
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.)
Ceased
Application number
PCT/EP2015/062877
Other languages
German (de)
English (en)
Inventor
Daniel Buchwald
Patrick BUCHWALD
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems 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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Publication of WO2015189234A1 publication Critical patent/WO2015189234A1/fr
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
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade

Definitions

  • the invention relates to the field of exhaust gas turbochargers for charging internal combustion engines. It relates to a compressor of a centrifugal compressor and an exhaust gas turbocharger with a compressor with such a compressor wheel.
  • single-stage centrifugal compressors are generally used to increase the intake pressure of the internal combustion engine.
  • the most widely used compressor wheels include a certain number of main blades and one idler blade per main blade.
  • a technology that both reduces product price and increases efficiency provides opportunities to dramatically increase the competitiveness of products across market segments.
  • No. 5,730,582 discloses a compressor wheel whose blades are shaped in such a way that the finished cast compressor wheel can be released from it without destruction of the casting mold.
  • the blades have a specially curved shape for this purpose.
  • the object of the present invention is to provide a compressor with an increased specific absorption capacity.
  • this is achieved by specifically increasing the narrowest cross-sectional area of the flow channels between the blades in the compressor wheel by means of a suitable blade shaping.
  • the blade leading edge of each main blade is configured sickle-shaped in the direction of the blade height, in that the blade is designed curved in the opposite direction to the direction of rotation. This enlarges the narrowest throat area between two adjacent blades.
  • the narrowest cross-sectional area is optionally further increased by bending the blade in the direction of rotation in the region of the throat line, where the narrowest cross-sectional area meets the suction side of the blade.
  • FIG. 1 shows an exhaust gas turbocharger with a radial compressor according to the prior art
  • FIG. 2 shows a compressor wheel of a radial compressor according to FIG. 1
  • FIG. 1 shows an exhaust gas turbocharger with a radial compressor according to the prior art
  • FIG. 2 shows a compressor wheel of a radial compressor according to FIG. 1
  • FIG. 1 shows an exhaust gas turbocharger with a radial compressor according to the prior art
  • FIG. 2 shows a compressor wheel of a radial compressor according to FIG. 1
  • FIG. 3 shows a schematic representation of two adjacently arranged blades of a compressor wheel according to FIG. 2, FIG.
  • FIG. 4 shows a schematic representation of two adjacently arranged blades according to a first exemplary embodiment of a compressor wheel designed according to the invention
  • FIG. 4 shows a schematic illustration of two adjacently arranged blades according to a second exemplary embodiment of a compressor wheel designed according to the invention.
  • FIG. 1 shows a section along the shaft axis through an exhaust gas turbocharger according to the prior art with a radial compressor and an axial turbine.
  • the compressor wheel 1 of the centrifugal compressor is arranged in a compressor housing 2 which limits the flow channels of the air required for combustion in the internal combustion engine.
  • the compressor wheel shown enlarged in FIG. 2 has a hub 10 and a multiplicity of moving blades.
  • the blades are subdivided into main blades 1 1 and 12, which have the full length, and intermediate vanes 15 arranged therebetween, which have an inlet edge which is offset in the direction of flow and thus a reduced length.
  • the term blades is used to refer to the main blades of the compressor wheel.
  • the compressor wheel is mounted on a shaft 4, which is mounted in a bearing housing 3 in the radial and axial directions.
  • the shaft and the compressor wheel attached to it are driven by the turbine wheel 6, which is arranged in a two-part turbine housing.
  • the hot exhaust gases from the combustion chambers of the internal combustion engine are passed through a gas inlet housing 8 on the turbine.
  • a guide device 7 Upstream of the rotor blades of the turbine wheel 6 is a guide device 7, which directs the flow onto the rotor blades.
  • the exhaust gases are supplied through the gas outlet housing 5 to the chimney or exhaust.
  • Each blade 12 of the compressor wheel 1 shown enlarged in Fig. 2 and shown schematically and in part in Fig. 3 has an inlet edge FE.
  • the surface on the pressure side (front of the blade in the direction of rotation) of each blade defines a flow channel.
  • This flow channel has a narrowest cross-sectional area 20, which usually intersects the pressure side of the blade 12 at the leading edge FE or at a certain distance from the leading edge FE.
  • the suction side of the next, adjacent blade cuts the narrowest cross-sectional area due to the oblique arrangement of the blades, however, with a greater distance from the leading edge, as shown in FIG. 2 can be seen.
  • the narrowest cross-sectional area 20 is referred to in the jargon as "Throat Area”, while the cut line TL on the suction side of the blade is commonly referred to as "Throat Line”.
  • the region of the leading edge of each blade is formed with a curvature in order to enlarge the throat area, ie the narrowest cross-sectional area 20 in the flow channel between the blades 11 and 12 of the compressor wheel.
  • the curvature goes against the direction indicated by the arrow running direction of the compressor wheel, so that the blade 12 is formed in the region of the leading edge FE to the pressure side and concave over the blade height. This results in an enlargement of the narrowest cross-sectional area 20 around the edge region designated 20 ' .
  • the concave curvature of the blade is then reduced in the direction of flow, ie from the leading edge in the direction of the trailing edge.
  • the blade changes into a flat shape, as shown in FIG. 4 by means of the auxiliary lines over the blade height.
  • the convex shape changes to the flat shape up to the throat line TL, so that the narrowest cross-sectional area is not reduced by the shape of the blade.
  • the second embodiment according to FIG. 5 goes even further.
  • the blade 12 is concave in the region of the inlet edge EL towards the pressure side and viewed over the blade height, so that the narrowest cross-sectional area in the area of the pressure side around the edge region 20 ' increases .
  • the blade does not just go into one flat shape, but undergoes a bend in the direction of rotation of the compressor wheel in the region of the throat line.
  • a concave shape results in the suction side over the blade height.
  • the narrowest cross-sectional area thus additionally increases in the edge region 20 " on the suction side.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un compresseur permettant d'obtenir un débit de dimensionnement élevé et comprenant une roue de compresseur (1) pourvue d'ailettes (11, 12). Dans la zone de l'écart le plus restreint (TL) entre deux ailettes (11, 12) adjacentes, les ailettes (11, 12) concernées sont déformées de telle manière que la surface (20',20'') délimitée par les deux ailettes (11, 12) dans la zone du point le plus étroit s'agrandit. Le bord avant (FE) de l'ailette est conçu en forme de croissant (20'), ce qui signifie que le bord avant (FE) est courbé à l'encontre du sens de rotation des ailettes (11, 12). La courbure est réduite au moins à une forme plane dans la direction d'écoulement jusqu'à la zone de l'écart le plus restreint (TL) entre deux ailettes (11, 12) adjacentes, de préférence même courbée (20'') dans le sens de rotation.
PCT/EP2015/062877 2014-06-12 2015-06-10 Compresseur permettant d'obtenir un débit de dimensionnement élevé Ceased WO2015189234A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014108268.0 2014-06-12
DE102014108268 2014-06-12

Publications (1)

Publication Number Publication Date
WO2015189234A1 true WO2015189234A1 (fr) 2015-12-17

Family

ID=53366035

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2015/062877 Ceased WO2015189234A1 (fr) 2014-06-12 2015-06-10 Compresseur permettant d'obtenir un débit de dimensionnement élevé

Country Status (1)

Country Link
WO (1) WO2015189234A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5730582A (en) * 1997-01-15 1998-03-24 Essex Turbine Ltd. Impeller for radial flow devices
EP1788255A1 (fr) * 2005-11-16 2007-05-23 Siemens Aktiengesellschaft Roue de compresseur radial
US20120263599A1 (en) * 2011-04-13 2012-10-18 Hitachi Plant Technologies, Ltd. Impeller and turbomachinery including the impeller
WO2012161849A1 (fr) * 2011-05-23 2012-11-29 Cameron International Corporation Hélice sculptée
DE102012004388A1 (de) * 2012-03-03 2013-09-05 Daimler Ag Verdichterrad für einen Verdichter, insbesondere einen Radialverdichter

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5730582A (en) * 1997-01-15 1998-03-24 Essex Turbine Ltd. Impeller for radial flow devices
EP1788255A1 (fr) * 2005-11-16 2007-05-23 Siemens Aktiengesellschaft Roue de compresseur radial
US20120263599A1 (en) * 2011-04-13 2012-10-18 Hitachi Plant Technologies, Ltd. Impeller and turbomachinery including the impeller
WO2012161849A1 (fr) * 2011-05-23 2012-11-29 Cameron International Corporation Hélice sculptée
DE102012004388A1 (de) * 2012-03-03 2013-09-05 Daimler Ag Verdichterrad für einen Verdichter, insbesondere einen Radialverdichter

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