WO2020125862A1 - Roue à aubes pour un turbocompresseur à gaz d'échappement et procédé de fabrication d'une roue de turbine - Google Patents

Roue à aubes pour un turbocompresseur à gaz d'échappement et procédé de fabrication d'une roue de turbine Download PDF

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Publication number
WO2020125862A1
WO2020125862A1 PCT/DE2019/101089 DE2019101089W WO2020125862A1 WO 2020125862 A1 WO2020125862 A1 WO 2020125862A1 DE 2019101089 W DE2019101089 W DE 2019101089W WO 2020125862 A1 WO2020125862 A1 WO 2020125862A1
Authority
WO
WIPO (PCT)
Prior art keywords
impeller
hub
exhaust gas
turbine wheel
indentation
Prior art date
Application number
PCT/DE2019/101089
Other languages
German (de)
English (en)
Inventor
Dominic König
David HEMBERGER
Original Assignee
Ihi Charging Systems International Gmbh
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 Ihi Charging Systems International Gmbh filed Critical Ihi Charging Systems International Gmbh
Publication of WO2020125862A1 publication Critical patent/WO2020125862A1/fr

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Classifications

    • 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
    • F01D5/027—Arrangements for balancing
    • 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
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • 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
    • F01D5/10—Anti- vibration means
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the invention relates to an impeller for an exhaust gas turbocharger of the type specified in the preamble of claim 1 and an exhaust gas turbocharger according to
  • Claim 7 Furthermore, the invention relates to a method for producing a turbine wheel according to claim 9.
  • exhaust gas turbochargers are now assigned to almost every internal combustion engine to increase performance.
  • the exhaust gas turbochargers have a section through which fresh air flows, and a section through which exhaust gas flows, each section having a wheel chamber for receiving an impeller in the form of a
  • Compressor wheel or a turbine wheel These two impellers are rotatably connected to each other with the help of a shaft.
  • the aim should be that
  • Exhaust gas turbocharger has a service life corresponding at least to the internal combustion engine.
  • the turbocharger is characterized by an extremely high compared to the internal combustion engine speed which is in the meantime well over 100,000 min -1. Due to the high centrifugal forces that occur during operation, this places high demands on the dielectric strength of the impellers of the exhaust gas turbocharger, since at the same time a fast response behavior of the exhaust gas turbocharger is required.
  • the wheel back has recesses to reduce the inertia of the impeller.
  • the recesses only partially extend in the axial direction over a wall thickness of the wheel back.
  • Exhaust gas turbocharger known, which is reduced in terms of its inertia with the help of a so-called scalopping.
  • Scalopping can lead to a reduction in the inertia of the impeller, but this mainly results in a reduction in the natural frequencies of the Impeller and an increase in dynamic tension due to vibrations of the impeller blades. Furthermore, there is an increased leakage flow between the impellers and the wall.
  • the invention is based on the object of an improved impeller for one
  • Exhaust gas turbocharger to specify. Furthermore, the invention is based on the object of specifying an exhaust gas turbocharger which is distinguished by a high degree of efficiency. Another object is to provide a method for manufacturing a turbine wheel.
  • An impeller according to the invention for an exhaust gas turbocharger comprises a hub and a plurality of impeller blades fixed on the hub, which are separated from one another
  • Exhaust gas turbocharger flowing medium are arranged around the hub.
  • a blade channel is formed between each two impeller blades, the blade channel having a blade channel length that starts from one
  • Hub back is designed to extend in the direction of a hub nose facing away from the hub back.
  • the blade channel has an indentation which extends in the radial direction, in the circumferential direction of the impeller and in the axial direction.
  • the impeller is preferably manufactured in a casting process, a material reduction, as a result of which the impeller can be manufactured more cost-effectively than an impeller of the prior art.
  • a flow behavior of the liquid material during the casting process can also be improved with a reduced hub thickness due to the indentation, so that, for example, a risk of so-called blowholes is substantially reduced. In other words, that means that
  • a major advantage of the impeller according to the invention can be seen in the fact that the three-dimensional indentation can be used to manipulate natural frequencies and natural forms of vibrations.
  • the resonances differ in the turbine wheel eigenforms.
  • the turbine therefore vibrates differently depending on the resonance.
  • Impeller blade can break off. With the help of the indentation, which can be designed accordingly, the vibration forms of the turbine can thus be changed and corresponding resonances avoided.
  • the indentation is designed to extend over a third of the blade channel length. Particularly in the area of a turbine wheel inlet, provided that the impeller is a turbine wheel, the indentation has a superior and effective effect on the inertia and
  • Vibration modes of the turbine can preferably be changed.
  • the indentation is designed to extend in the radial direction from a first diameter of the impeller to a second diameter of the impeller, the second diameter corresponding to half the first diameter.
  • the indentation is advantageously concave in relation to a longitudinal axis of the impeller, as a result of which residual stresses due to the indentation are reduced.
  • Another advantage of the concave design of the indentation is the favorable demolding of the impeller after the casting process.
  • the indentation is formed to extend in the circumferential direction from a first transition edge to a second transition edge.
  • the advantage is an increased reduction in inertia and a lower notch effect for centrifugal stresses.
  • the impeller is a turbine wheel. In particular with turbine wheels, the invention has
  • Operating area has a larger number of resonance points than compressor wheels, which may also be caused by so-called pre-grille.
  • Waveforms are so pronounced that particularly advantageous turbine wheels can be formed with the aid of the indentation.
  • Another aspect of the invention relates to an exhaust gas turbocharger, with a
  • Air guide section wherein in the exhaust gas guide section a turbine wheel is rotatably received in a wheel chamber of the exhaust gas guide section, and wherein in the air guide section a compressor wheel is rotatably received in a wheel chamber of the air guide section, and wherein the turbine wheel is rotatably connected to the compressor wheel.
  • at least the turbine wheel is designed according to claims 1 to 6. The advantage is to be seen in the significantly improved response behavior of a rotor having the impeller, in particular the turbine wheel. As a result, the exhaust gas turbocharger can be operated quickly in a favorable efficiency range, which results in a reduction of
  • the compressor wheel which has the running gear, the compressor wheel for weight reduction being made of an aluminum-containing and / or titanium-containing and / or magnesium-containing material.
  • the compressor wheel can also have the features of claims 1 to 5, whereby another
  • FIG. 1 is a perspective view of a hub of an impeller according to the prior art
  • Fig. 2 is a perspective view of the hub of an inventive
  • FIG. 3 in a perspective sectional view of a section of
  • FIG. 4 is a perspective view of a section of the impeller according to the invention.
  • FIG. 5 is a perspective sectional view of a section of the impeller according to the prior art.
  • FIG. 6 shows a perspective sectional view of a section of the impeller according to FIG. 3.
  • the hub 1 shows a hub 1 of an impeller 2 according to the prior art.
  • the hub 1 is designed in the shape of a truncated cone in accordance with a typical radial wheel, a disk-shaped hub back 3 being connected to a truncated cone 4 and a transition 5 formed between the back of the hub 3 and the truncated cone 4 tangentially to both parts 3, 4 to form a usually variable radius R. is approximately formed.
  • the hub 1 has a hub lug 23.
  • the hub 1 has an essentially flat outer surface 6.
  • a flat outer surface 6 is to be understood as a rotationally symmetrical outer surface 6 which has a continuous and differentiable course in the direction of a longitudinal axis 7 of the impeller 2 and over its circumference.
  • the impeller 2 is designed in the form of a turbine wheel for a turbine, not shown, in particular a radial turbine, of an exhaust gas turbocharger 24 for an internal combustion engine, not shown.
  • the turbine is arranged in an exhaust tract of the internal combustion engine, not shown, with With the help of the turbine wheel, exhaust gas expelled from the internal combustion engine is expanded to drive a compressor (not shown)
  • FIG. 2 the hub 1 of an impeller 2 according to the invention is shown in a perspective view.
  • the hub 1 has indentations 8, which are predominantly formed on the hub back 3 and extend over the transition 5 in the direction of the
  • Truncated cone 4 are designed to extend.
  • the hub 1 has a plurality of impeller blades 9 which are fixedly connected to the hub 1, see FIG. Figures 3 to 6.
  • the hub 1 has a not shown
  • the indentations 8 are distinguished in that they have a radial first distance A1 from the longitudinal axis 7 at at least one axial point XA, which is smaller than a radial second distance A2 from the longitudinal axis 7 of a
  • Blade base 20 wherein the blade base 20 corresponds to the lateral surface 6 in the area of an impeller blade 9.
  • Embodiment formed integrally with each other.
  • a blade channel 10 is formed between each two adjacent impeller blades 9 ′.
  • the blade channel 10 has a blade channel length SL which extends in the axial direction of the impeller 2.
  • the indentations 8 are formed in the blade channel 10 in a radial, axial and circumferential direction.
  • the indentations are formed symmetrically between a pressure side of the rotor blade 9 ′ and a suction side of the adjacent rotor blade 9 ′′. They could also be asymmetrical. This depends on different factors, such as, for example, a blade curvature, number of blades or hub diameter and an area of application of the turbine wheel 2.
  • the plurality of impeller blades 9 are connected to the hub 1 both on their suction side 22 and on their pressure side 21 via a first transition region 11 on the pressure side 21 and via a second transition region 12 on the suction side 22, as shown in particular in FIG. 5 is.
  • the first transition region 11 and the second transition region 12 are formed on the lateral surface 6 both over the circumference of the hub 1 and over the axial extent of the hub 1 along the longitudinal axis 7. Basically, for general explanation of the
  • Transition areas 1 1, 12 are said to be distinguished by the fact that they form a rounded connection between the plurality of impeller blades 9 and the hub 1. In other words, with the help of
  • Transitional areas 1 1, 12 discontinuities, such as angular transitions, in the
  • the indentation 8 is concave between the first transition region 11 and the second transition region 12 relative to the longitudinal axis 7.
  • the indentation 8 is shown in dashed lines in FIG. 5 so that its course with respect to the hub 1 can be recognized according to the prior art.
  • the indentation 8 preferably extends over a third of the blade channel 10. In other words, that means that a length L of the indentation 8 in particular a third of the
  • Blade channel length SL corresponds.
  • the indentation 8 extends from its largest first circumferential edge 13, which is formed at a first diameter D1 of the impeller 2, to its smallest second circumferential edge 14, which is formed at a second diameter D2 of the impeller 2, the first diameter D1 is twice as large as the second diameter D2.
  • a first longitudinal edge 15 of the indentation 8 and a second longitudinal edge 16 of the indentation 8 each correspond to the one facing them
  • the first peripheral edge 13 has an edge distance A from an outer edge 19 of the hub back 3. Likewise, as in the first
  • a method according to the invention for producing a turbine wheel 2 is characterized in that
  • a turbine wheel shape is determined, for example by a numerical method or by tests,
  • an oscillation form is analyzed, for example by an analysis of the dynamic stress distribution due to the oscillation, and
  • the indentation 8 which extends in the radial direction, in the circumferential direction and in the axial direction, is introduced into the blade duct 10 of the turbine wheel 2.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une roue à aubes pour un turbocompresseur à gaz d'échappement, comprenant un moyeu (1) et une pluralité d'aubes de roue à aubes (9) fixées sur le moyeu, qui sont disposées sur le moyeu (1) de telle sorte qu'un fluide s'écoulant à travers le turbocompresseur à gaz d'échappement (24) peut circuler autour d'elles, et, entre respectivement deux aubes de roue à aubes (9), un canal d'aube (10) étant formé, le canal d'aube (10) présentant une longueur de canal d'aube (SL), la longueur de canal d'aube (SL) s'étendant d'un arrière de moyeu (3) dans la direction d'un nez de moyeu (23) opposé à l'arrière de moyeu (3). Selon l'invention, le canal d'aube (10) comporte une rainure (8) s'étendant dans la direction radiale, dans la direction circonférentielle de la roue à aubes (2) et dans la direction axiale. L'invention concerne en outre un turbocompresseur à gaz d'échappement (24) ainsi qu'un procédé de fabrication d'une roue de turbine.
PCT/DE2019/101089 2018-12-17 2019-12-16 Roue à aubes pour un turbocompresseur à gaz d'échappement et procédé de fabrication d'une roue de turbine WO2020125862A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102018132535.5A DE102018132535A1 (de) 2018-12-17 2018-12-17 Laufrad für einen Abgasturbolader, Abgasturbolader und Verfahren zur Herstellung eines Turbinenrades
DE102018132535.5 2018-12-17

Publications (1)

Publication Number Publication Date
WO2020125862A1 true WO2020125862A1 (fr) 2020-06-25

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PCT/DE2019/101089 WO2020125862A1 (fr) 2018-12-17 2019-12-16 Roue à aubes pour un turbocompresseur à gaz d'échappement et procédé de fabrication d'une roue de turbine

Country Status (2)

Country Link
DE (1) DE102018132535A1 (fr)
WO (1) WO2020125862A1 (fr)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006114007A1 (fr) 2005-04-27 2006-11-02 Abb Turbo Systems Ag Roue de turbine
US20110064580A1 (en) * 2009-09-16 2011-03-17 United Technologies Corporation Turbofan flow path trenches
WO2014046927A1 (fr) 2012-09-19 2014-03-27 Borgwarner Inc. Roue de turbine
US20150086395A1 (en) * 2012-04-23 2015-03-26 Borgwarner Inc. Turbocharger blade with contour edge relief and turbocharger incorporating the same
US20160017796A1 (en) * 2013-02-21 2016-01-21 United Technologies Corporation Gas turbine engine having a misturned stage
EP3032033A1 (fr) * 2014-12-08 2016-06-15 United Technologies Corporation Ensemble de vanne pour moteur de turbine à gaz
DE102014226477A1 (de) * 2014-12-18 2016-06-23 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader
US20160363134A1 (en) * 2014-03-05 2016-12-15 Mitsubishi Heavy Industries, Ltd. Rotary fluid element and method of correcting unbalance of rotary fluid element
DE102016112521A1 (de) * 2016-07-07 2018-01-11 Ihi Charging Systems International Germany Gmbh Laufrad für einen Abgasturbolader, Abgasturbolader und Verfahren zum Auswuchten eines Laufzeugs für einen Abgasturbolader

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006114007A1 (fr) 2005-04-27 2006-11-02 Abb Turbo Systems Ag Roue de turbine
US20110064580A1 (en) * 2009-09-16 2011-03-17 United Technologies Corporation Turbofan flow path trenches
US20150086395A1 (en) * 2012-04-23 2015-03-26 Borgwarner Inc. Turbocharger blade with contour edge relief and turbocharger incorporating the same
WO2014046927A1 (fr) 2012-09-19 2014-03-27 Borgwarner Inc. Roue de turbine
US20160017796A1 (en) * 2013-02-21 2016-01-21 United Technologies Corporation Gas turbine engine having a misturned stage
US20160363134A1 (en) * 2014-03-05 2016-12-15 Mitsubishi Heavy Industries, Ltd. Rotary fluid element and method of correcting unbalance of rotary fluid element
EP3032033A1 (fr) * 2014-12-08 2016-06-15 United Technologies Corporation Ensemble de vanne pour moteur de turbine à gaz
DE102014226477A1 (de) * 2014-12-18 2016-06-23 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader
DE102016112521A1 (de) * 2016-07-07 2018-01-11 Ihi Charging Systems International Germany Gmbh Laufrad für einen Abgasturbolader, Abgasturbolader und Verfahren zum Auswuchten eines Laufzeugs für einen Abgasturbolader

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