EP3128181A1 - Roue de compresseur pour une turbosoufflante de gaz d'echappement - Google Patents

Roue de compresseur pour une turbosoufflante de gaz d'echappement Download PDF

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Publication number
EP3128181A1
EP3128181A1 EP16181125.2A EP16181125A EP3128181A1 EP 3128181 A1 EP3128181 A1 EP 3128181A1 EP 16181125 A EP16181125 A EP 16181125A EP 3128181 A1 EP3128181 A1 EP 3128181A1
Authority
EP
European Patent Office
Prior art keywords
compressor wheel
transition
base
wheel according
blades
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP16181125.2A
Other languages
German (de)
English (en)
Other versions
EP3128181B1 (fr
Inventor
Senol Sögüt
Felix SCHEERER
Martin Kuhn
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.)
BMTS Technology GmbH and Co KG
Original Assignee
Bosch Mahle Turbo Systems GmbH and Co KG
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 Bosch Mahle Turbo Systems GmbH and Co KG filed Critical Bosch Mahle Turbo Systems GmbH and Co KG
Publication of EP3128181A1 publication Critical patent/EP3128181A1/fr
Application granted granted Critical
Publication of EP3128181B1 publication Critical patent/EP3128181B1/fr
Active 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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • 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
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F05D2250/611—Structure; Surface texture corrugated undulated
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/73—Shape asymmetric

Definitions

  • the present invention relates to a compressor wheel for an exhaust gas turbocharger with a hub body and arranged thereon blades according to the preamble of claim 1.
  • the invention also relates to an exhaust gas turbocharger with such a compressor wheel.
  • compressor wheels consist of a hub base body and the blade leaves arranged thereon, wherein modern compressor wheels are usually equipped with a backward curved compressor wheel outlet for thermodynamic reasons.
  • This backward curvature leads under the influence of centrifugal force on a suction side in the connection region of the blades to the hub body to high tensile stresses, which reduce life expectancy.
  • a higher speed and / or an even stronger reverse curvature are / is only possible to a limited extent for reasons of service life.
  • the hub base bodies commonly used today are designed as round solid rotary body, this simple geometry is not ideal in terms of the particular occurring in a transition between the airfoil and the hub body load. Also by an increase in a radius in the transition between the blade and the hub body, this can only partially remedy be created because the highest load often occurs not in the transition itself, but in the hub body at the outlet of the transition.
  • the present invention therefore deals with the problem of designing a compressor wheel in such a way that, on the one hand, it is weight-optimized and, on the other hand, it is designed to be optimized in terms of receiving possible loads.
  • the present invention is based on the general idea of changing a hub body of a compressor wheel for an exhaust-gas turbocharger, which has hitherto been designed as a round rotary body, with respect to its shape in such a way that, in particular, critical load areas, for example in a transition between the hub base body and blade leaves arranged thereon, are effectively relieved can, without the compressor wheel itself would have to be much more massive and thus heavier.
  • two embodiments are available for selection, wherein in the first of the hub base body is formed as a polygon with a number of blades corresponding number of mutually tilted segments and alternatively wherein the hub body has a blade facing the blades and circumferentially wavy base surface, in which case a Number of waves corresponds to a number of blades.
  • Both embodiments have in common that the hub base body is changed in particular in the region of the transition to an airfoil so that it, the stresses occurring there, in particular tensile stresses due to a backward curvature of the individual Airfoils better able to absorb, which not only the performance, but also the life of such a compressor wheel can be increased.
  • the individual segments have radially outside a cross-sectionally straight base.
  • the hub base body is thus designed as a polygon with a number of segments corresponding to the number of individual airfoils, wherein these segments each have a straight base surface and merge into one another like a sawtooth radially on the outside.
  • a transition from a segment to an associated airfoil is rounded.
  • the rounded transition is formed by a material addition to the base surface of the respective segment.
  • each a slight accumulation of material is provided, which is sufficient to take over the increased stresses occurring there, but in comparison to a fully reinforced hub base body only a local material order represents and thereby designed the compressor according to the invention much easier.
  • a transition from the base surface into an associated airfoil in the region of a wave crest is arranged.
  • said transition is formed in the base, for example, by a tangent to a wave slope.
  • the hub body has a ripple in the circumferential direction on.
  • a number of waves on the back of the hub body may correspond to a number of blades on the opposite front.
  • the base surface or the hub base body can be stiffened by the wavy shape and at the same time can be made material-optimized with regard to the stresses occurring. Due to the wavy back of the hub base body locally occurring stresses, which usually occur under the blades on Rabine be reduced. The advantage of a wavy wheel back is the local material application at heavily loaded areas. This allows a mass-effective reduction of stress without unnecessary weight gain.
  • the present invention is further based on the general idea of equipping an exhaust gas turbocharger with such a previously mentioned compressor wheel, wherein a significantly improved response of the exhaust gas turbocharger can be achieved by the compressor wheel according to the invention, which is significantly lighter due to the low local material application than previously fully thickened compressor wheels can.
  • the life of the entire exhaust gas turbocharger can be extended because of the extension of the life of the compressor wheel no bursting thereof and thus damage to a compressor housing must be feared.
  • the wave crests run radially inward and / or radially outward and go in alignment in the base, so that no wave crests are present at a Ver emphasizerradeintritt and a Ver emphasizerradaustritt.
  • waves or wave crests are arranged exclusively at those points where it also require the occurring loads. In this way, a load-optimized and at the same time weight-optimized compressor wheel can be created.
  • thermodynamic disadvantages can be avoided.
  • a compressor wheel 1 according to the invention for an exhaust-gas turbocharger 2 has a hub base body 3 and airfoils 4 arranged thereon.
  • Fig. 1 only the hub body 3, but not the associated blades 4 are shown.
  • two alternative embodiments of the hub body 3 are provided, wherein a first alternative in the Fig. 1 and 2 and the second alternative in the Fig. 3 to 5 are shown.
  • the hub body 3 according to the invention as a polygon with a number of the number of blades 4 corresponding number of mutually tilted segments 5 formed.
  • the individual segments 5 (compare also the FIG. 2 ) preferably have at least radially outside a cross-sectionally straight base surface 6, which may vary depending on the requirements of the hub body 3 and the respective blade 4 and also tilted to each other.
  • the transition 7 from a segment 5 into an associated airfoil 4 is preferably rounded, wherein the fillet or the rounded transition 7 is formed by a material addition 8, that is to say an additional material application, to the base surface 6 of the respective segment 5.
  • the hub base body 3 here has a base plate 6 facing the blades and wavy in the circumferential direction, wherein a number of individual waves 10 corresponds to a number of blades 4.
  • a back of the base 6 and the hub body 3 is formed wavy, the waves 10 of the back 9 and the base 6 are parallel.
  • the back 9 without such waves that is just be formed, in this context, the back 9 on the hub body 3 of the compressor wheel 1 according to the Fig. 1 and 2 straight or can be formed with waves 10.
  • a transition 7 from the base 6 into an associated airfoil 4 is preferably arranged in the region of a wave crest 11 or at least slightly adjacent thereto.
  • a transition 7 between the wavy base 6 and the associated blade 4 is rounded, as shown in the Fig. 3 is shown with a broken drawn line, wherein such a rounded transition 7 passes through an applied to a wave slope 12 tangent in the base 6.
  • a tangential transition into the associated airfoil 4 can be achieved.
  • the wave crests 11 leak radially inward and / or radially outward and pass into the base surface 6, so that no wave crests 11 are present at a compressor wheel inlet 13 and a compressor wheel outlet 14.
  • Figure 4 the original course of a compressor wheel according to the prior art is drawn with a solid line, while the course of the compressor wheel 1 according to the invention is shown in the region of the wave crest 11 with a dotted line.
  • the hub body 3 has in a compressor 1 according to the FIGS. 4 and 5 a flat back 9.
  • the radial position of the wave peaks 11 can be calculated in relation to the compressor wheel size (compressor wheel radius) from the quotient "radius VR / position It has been found that the wave crest 11 is between 1.1 and 2.2 relative to the radius R VR of the compressor wheel 1. For a ratio of a radius R VR of the compressor wheel 1 to a maximum radial extent R WB of wave crest 11 is therefore valid 1 . 1 ⁇ R VR / R WB . ⁇ 2 . 2
  • the thickening, in particular material additions 8, of the wave crests 11 is thus present only in the intermediate region between two adjacent blade leaves 4.
  • the course looks different. For all gradients, however, it is the same that they are not rotationally symmetrical and go back to the original, rotationally symmetrical hub profile both in the direction of the compressor wheel step 13 and in the direction of the compressor wheel outlet 14. As a result, thermodynamic disadvantages can be avoided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16181125.2A 2015-08-04 2016-07-26 Roue de compresseur pour une turbocompresseur de gaz d'echappement Active EP3128181B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015214854.8A DE102015214854A1 (de) 2015-08-04 2015-08-04 Verdichterrad für einen Abgasturbolader

Publications (2)

Publication Number Publication Date
EP3128181A1 true EP3128181A1 (fr) 2017-02-08
EP3128181B1 EP3128181B1 (fr) 2019-09-04

Family

ID=56550136

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16181125.2A Active EP3128181B1 (fr) 2015-08-04 2016-07-26 Roue de compresseur pour une turbocompresseur de gaz d'echappement

Country Status (4)

Country Link
US (1) US10689982B2 (fr)
EP (1) EP3128181B1 (fr)
CN (1) CN106438461B (fr)
DE (1) DE102015214854A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3470626A1 (fr) * 2017-10-12 2019-04-17 Borgwarner Inc. Turbocompresseur à suralimentation avec roue de turbine amélioré
DE102023126038A1 (de) * 2023-09-26 2025-03-27 Ebm-Papst St. Georgen Gmbh & Co. Kg Lüfterrad mit einer eine Welligkeit aufweisenden Begrenzungsfläche sowie Lüfter mit einem solchen Lüfterrad

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20190099239A (ko) * 2016-12-23 2019-08-26 보르그워너 인코퍼레이티드 터보 차저 및 터빈 휠
DE102019211515A1 (de) 2019-08-01 2021-02-04 Vitesco Technologies GmbH Turbinenlaufrad einer Abgasturbine und Abgasturbolader für eine Brennkraftmaschine
DE102021133773B3 (de) 2021-12-18 2023-02-09 Borgwarner Inc. Verdichterrad
DE102021133772B3 (de) * 2021-12-18 2023-01-19 Borgwarner Inc. Verdichterrad

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1002707A (fr) * 1948-12-14 1952-03-10 Belliss & Morcom Ltd Perfectionnements aux pompes centrifuges, compresseurs d'air ou autres gaz et appareils analogues
US5215439A (en) * 1991-01-15 1993-06-01 Northern Research & Engineering Corp. Arbitrary hub for centrifugal impellers
JP2008163760A (ja) * 2006-12-27 2008-07-17 Ihi Corp ラジアルインペラ、過給機
US20120269636A1 (en) * 2011-04-25 2012-10-25 Honeywell International Inc. Blade features for turbocharger wheel
WO2014015959A1 (fr) * 2012-07-26 2014-01-30 Ihi Charging Systems International Gmbh Roue à aubes destinée à une machine à fluide
US8721287B2 (en) 2008-05-15 2014-05-13 Turbomeca Compressor impeller blade with variable elliptic connection

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2918254A (en) * 1954-05-10 1959-12-22 Hausammann Werner Turborunner
EP0567589A1 (fr) * 1991-01-15 1993-11-03 NORTHERN RESEARCH & ENGINEERING CORPORATION Moyeu arbitraire pour roue a aubes
US6471474B1 (en) * 2000-10-20 2002-10-29 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
CN101666326B (zh) * 2008-09-04 2011-08-17 杨圣安 组合式叶轮
JP2011021491A (ja) * 2009-07-13 2011-02-03 Mitsubishi Heavy Ind Ltd インペラおよび回転機械
JP2011021492A (ja) * 2009-07-13 2011-02-03 Mitsubishi Heavy Ind Ltd インペラおよび回転機械
CN102667172B (zh) * 2009-10-08 2018-11-02 苏尔寿管理有限公司 泵叶轮

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1002707A (fr) * 1948-12-14 1952-03-10 Belliss & Morcom Ltd Perfectionnements aux pompes centrifuges, compresseurs d'air ou autres gaz et appareils analogues
US5215439A (en) * 1991-01-15 1993-06-01 Northern Research & Engineering Corp. Arbitrary hub for centrifugal impellers
JP2008163760A (ja) * 2006-12-27 2008-07-17 Ihi Corp ラジアルインペラ、過給機
US8721287B2 (en) 2008-05-15 2014-05-13 Turbomeca Compressor impeller blade with variable elliptic connection
US20120269636A1 (en) * 2011-04-25 2012-10-25 Honeywell International Inc. Blade features for turbocharger wheel
WO2014015959A1 (fr) * 2012-07-26 2014-01-30 Ihi Charging Systems International Gmbh Roue à aubes destinée à une machine à fluide

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3470626A1 (fr) * 2017-10-12 2019-04-17 Borgwarner Inc. Turbocompresseur à suralimentation avec roue de turbine amélioré
DE102023126038A1 (de) * 2023-09-26 2025-03-27 Ebm-Papst St. Georgen Gmbh & Co. Kg Lüfterrad mit einer eine Welligkeit aufweisenden Begrenzungsfläche sowie Lüfter mit einem solchen Lüfterrad

Also Published As

Publication number Publication date
CN106438461A (zh) 2017-02-22
CN106438461B (zh) 2021-02-09
US10689982B2 (en) 2020-06-23
US20170037729A1 (en) 2017-02-09
EP3128181B1 (fr) 2019-09-04
DE102015214854A1 (de) 2017-02-09

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