EP1875045A1 - Roue de turbine - Google Patents

Roue de turbine

Info

Publication number
EP1875045A1
EP1875045A1 EP06705416A EP06705416A EP1875045A1 EP 1875045 A1 EP1875045 A1 EP 1875045A1 EP 06705416 A EP06705416 A EP 06705416A EP 06705416 A EP06705416 A EP 06705416A EP 1875045 A1 EP1875045 A1 EP 1875045A1
Authority
EP
European Patent Office
Prior art keywords
hub
turbine wheel
blade
scalloping
turbine
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
EP06705416A
Other languages
German (de)
English (en)
Other versions
EP1875045B1 (fr
Inventor
Martin Seiler
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
Priority to EP06705416A priority Critical patent/EP1875045B1/fr
Publication of EP1875045A1 publication Critical patent/EP1875045A1/fr
Application granted granted Critical
Publication of EP1875045B1 publication Critical patent/EP1875045B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/04—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
    • F01D5/02—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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • 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
    • 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
    • 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

Definitions

  • the invention relates to the field of exhaust gas turbochargers. It relates to a turbine wheel of a radial or mixed-flow turbine with the features of the preamble of the independent claim.
  • Compact exhaust gas turbochargers generally have exhaust gas turbines flowed through strictly radially (radial turbine) or diagonally (mixed-flow turbine).
  • the exhaust gas flow is deflected by the turbine wheel and flows in the axial direction.
  • the turbine wheels of radial and mixed-flow turbines are often provided with a scalloping.
  • the scalloping refers to a recess in the rear wall of the hub of the turbine wheel between the individual blades.
  • the main purpose of scalloping is to reduce the mass moment of inertia by cutting out material in the radially outermost region of the turbine wheel.
  • the scalloping contour can be formed symmetrically with respect to the exhaust gas inlet edge of the individual rotor blades of the turbine wheel.
  • the scalloping contour runs pointed or rounded towards the exhaust gas inlet edge.
  • the scalloping contour is usually also rounded so that it comes from the exhaust gas inlet edge to exhaust gas inlet edge of adjacent blades to a continuously extending scalloping contour.
  • the scalloping contour can take an asymmetrical course between the exhaust gas inlet edges of adjacent rotor blades.
  • the blades are three-dimensionally curved.
  • the respective hub cut ie the transition of a blade to the hub, with respect to the radial on a curved course.
  • the hub in the area against the radially outermost edge is inclined backwards to the turbine shaft. Due to the three-dimensional blade shape, asymmetric deformation in the area of the scalloping can occur at high speed and the thermal loading of the turbine wheel.
  • the rear wall of the hub in the case of a symmetrical scalloping contour as shown in Fig. 2 is pulled radially outwardly by the strong centrifugal forces.
  • the surface on the pressure side of the blade rotates about the foot of the blade, as indicated by the thick arrow in the figure. This creates high voltages in the area of the scalloping contour, in particular in the lowest point, which can be life-limiting for the turbine wheel in extreme cases.
  • the object of the present invention is to provide a turbine wheel with three-dimensionally curved blades and scalloping in the region of the hub rear wall, in which the stresses occurring due to scalloping deformations are reduced during operation.
  • the blade is moved with respect to the scalloping contour to the pressure side.
  • the exhaust-gas inlet edge of the blade which is bent toward the pressure side, is thus not at the highest point of the scalloping contour, but is displaced toward the pressure side.
  • the hub section of the blade divides the area bounded by the scalloping contour surface of the rear wall of the shaft hub in two equal 'faces. The load of the two partial surfaces with respect to Deformation during operation is thereby aligned and the unilateral maximum load is reduced.
  • FIG. 1 shows a turbine wheel embodied under load according to the invention, with a turbine wheel displaced with respect to the point of symmetry of the scalloping contour, with the exhaust gas inlet edges of the rotor blades being displaced,
  • FIG. 2 shows a turbine wheel according to the prior art, shown under load, with exhaust gas inlet edges of the rotor blades arranged at the point of symmetry of the scalloping contour
  • Fig. 3 is a schematic representation of the rear wall of the hub of the turbine wheel of FIG. 1 in an axially guided section
  • Fig. 4 is a schematic representation of the rear wall of the hub of the turbine wheel of Fig. 3 in a guided along the hub surface (IV-IV) section.
  • the turbine wheel according to FIG. 1 has a hub 15 and a plurality of rotor blades 14 arranged around the hub.
  • the hub is arranged at the end of a rotatably mounted in the housing of an exhaust gas turbocharger turbine shaft 2.
  • the hub may be connected to the turbine shaft material fit or via a threaded connection.
  • At the other end of the turbine shaft an unillustrated compressor wheel is arranged.
  • the turbine wheel drives the compressor wheel.
  • the illustrated turbine wheel of a mixed-flow turbine has only a few blades. The number of blades can be freely selected depending on the operating requirements.
  • the inlet edges 16 of the blades of the turbine wheel are arranged perpendicular to the flow direction in the mixed-flow turbine.
  • the leading edge is not inclined as in the radial turbine perpendicular to the radial, but at an angle to the radial.
  • the rear wall of the hub is inclined to the radially outermost region of the turbine wheel towards the turbine shaft educated. This radially outermost region of the hub has a scalloping contour, ie in each case between two blades, material is cut out from the hub rear wall.
  • the blades and the hub of the turbine wheel are typically cast or milled in one piece, i. the blades are firmly connected to the hub. in the
  • Blade contour and hub shell .
  • r For a more understandable explanation of
  • the hub cut 12 is reduced in the figures on a line. In FIG. 4, however, in addition to the hub cut 12, the effective course of the cut curve between blade contour and hub surface is also indicated.
  • the hub cut 12 thus has a double-curved course according to FIGS. 3 and 4.
  • the rotor blades of the turbine wheel according to the invention are arranged with respect to the scalloping contour 11 such that the surfaces of the hub rear wall are uniformly supported on both sides of the rotor blades. This can be explained simply with reference to FIG. 4.
  • This rotation can also be seen in the representation of the turbine wheel according to the state of the art - FIG. 2 - clearly illustrated by an arrow.
  • the ⁇ figure shows a turbine under load, so that the centrifugal forces caused by the Deformations are made visible.
  • the radially outermost edge of the hub of the turbine wheel is loaded due to this rotation with a high voltage.
  • the two surfaces Fi and F 2 are aligned with each other.
  • the two surfaces are delimited by the scalloping contour 11 on the one hand, and by a connecting line between the radially inwardmost points A and B of the scalloping contour on the suction side and pressure side of the blade.
  • the curved hub cut 12 now runs through the middle of the two surfaces and supports them optimally.
  • the rotations due to the centrifugal forces are smaller and the turbine wheel is exposed to lower voltages.
  • These minor rotations are also shown in the illustration of the turbine wheel according to the invention according to FIG.
  • the two arrows indicate the slight deformations.
  • the figure shows the turbine wheel under the same load as the turbine wheel according to FIG. 2.
  • the radially outermost edge of the hub of the turbine wheel is loaded with significantly lower tension because of these minor twists.
  • the exact extent of the displacement of the blade with respect to the scalloping contour depends on various factors. For example, the curvature of the hub cut and the exact shape of the scalloping contour is important.
  • the scalloping contour of the illustrated turbine wheels has a symmetrical, wave-shaped course.
  • the scalloping contour can also have an asymmetrical course and can run approximately matched to the course of the blade in the region of the hub section.

Landscapes

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

Abstract

Roue (1) de turbine qui comporte un moyeu (15) et des aubes (14), chaque aube (14) étant reliée au moyeu le long d'une rainure incurvée (12) dans le moyeu. Les aubes sont ainsi conçues et placées sur le moyeu que la rainure (12) dans le moyeu s'étend de manière incurvée en s'écartant de l'orientation radiale, vers le côté de pression de l'aube, et le moyeu possède entre deux aubes voisines, dans la zone de la paroi arrière du moyeu, un contour (11) en forme de dentelure. La rainure (12) dans le moyeu de chaque aube (14) est placée par rapport à la surface dentelée (F1 + F2) de manière telle que cette surface s'appuie de manière aussi symétrique que possible sur l'aube. La roue de turbine selon la présente invention à aubes incurvées en trois dimensions et dentelure dans la zone de la paroi arrière du moyeu présente ainsi moins de tensions dues aux déformations des dentelures .
EP06705416A 2005-04-27 2006-03-24 Roue de turbine Active EP1875045B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06705416A EP1875045B1 (fr) 2005-04-27 2006-03-24 Roue de turbine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05405319A EP1717414A1 (fr) 2005-04-27 2005-04-27 Roue de turbine
PCT/CH2006/000176 WO2006114007A1 (fr) 2005-04-27 2006-03-24 Roue de turbine
EP06705416A EP1875045B1 (fr) 2005-04-27 2006-03-24 Roue de turbine

Publications (2)

Publication Number Publication Date
EP1875045A1 true EP1875045A1 (fr) 2008-01-09
EP1875045B1 EP1875045B1 (fr) 2008-12-17

Family

ID=35695045

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05405319A Withdrawn EP1717414A1 (fr) 2005-04-27 2005-04-27 Roue de turbine
EP06705416A Active EP1875045B1 (fr) 2005-04-27 2006-03-24 Roue de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP05405319A Withdrawn EP1717414A1 (fr) 2005-04-27 2005-04-27 Roue de turbine

Country Status (8)

Country Link
US (1) US7771170B2 (fr)
EP (2) EP1717414A1 (fr)
JP (1) JP4718599B2 (fr)
KR (1) KR101184952B1 (fr)
CN (1) CN101166890B (fr)
DE (1) DE502006002383D1 (fr)
RU (1) RU2007143991A (fr)
WO (1) WO2006114007A1 (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE112013001877T5 (de) 2012-05-03 2014-12-31 Borgwarner Inc. Superback-Rad mit reduzierter Spannung
US20150283656A1 (en) * 2012-11-02 2015-10-08 Borgwarner Inc. Process for producing a turbine wheel
US10066639B2 (en) 2015-03-09 2018-09-04 Caterpillar Inc. Compressor assembly having a vaneless space
US9890788B2 (en) 2015-03-09 2018-02-13 Caterpillar Inc. Turbocharger and method
US9879594B2 (en) 2015-03-09 2018-01-30 Caterpillar Inc. Turbocharger turbine nozzle and containment structure
US9739238B2 (en) 2015-03-09 2017-08-22 Caterpillar Inc. Turbocharger and method
US9903225B2 (en) 2015-03-09 2018-02-27 Caterpillar Inc. Turbocharger with low carbon steel shaft
US9822700B2 (en) 2015-03-09 2017-11-21 Caterpillar Inc. Turbocharger with oil containment arrangement
US9650913B2 (en) 2015-03-09 2017-05-16 Caterpillar Inc. Turbocharger turbine containment structure
US9638138B2 (en) 2015-03-09 2017-05-02 Caterpillar Inc. Turbocharger and method
US9777747B2 (en) 2015-03-09 2017-10-03 Caterpillar Inc. Turbocharger with dual-use mounting holes
US9810238B2 (en) 2015-03-09 2017-11-07 Caterpillar Inc. Turbocharger with turbine shroud
US9683520B2 (en) 2015-03-09 2017-06-20 Caterpillar Inc. Turbocharger and method
US9915172B2 (en) 2015-03-09 2018-03-13 Caterpillar Inc. Turbocharger with bearing piloted compressor wheel
US10006341B2 (en) 2015-03-09 2018-06-26 Caterpillar Inc. Compressor assembly having a diffuser ring with tabs
US9732633B2 (en) 2015-03-09 2017-08-15 Caterpillar Inc. Turbocharger turbine assembly
US9752536B2 (en) 2015-03-09 2017-09-05 Caterpillar Inc. Turbocharger and method
DE102018132535A1 (de) 2018-12-17 2020-06-18 Ihi Charging Systems International Gmbh Laufrad für einen Abgasturbolader, Abgasturbolader und Verfahren zur Herstellung eines Turbinenrades
US11885238B2 (en) * 2021-12-03 2024-01-30 Garrett Transportation I Inc. Turbocharger turbine wheel

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GB514420A (en) * 1937-06-07 1939-11-07 Ferdinando Carlo Reggio Improvements in or relating to centrifugal blowers or compressors
US3040670A (en) * 1959-10-16 1962-06-26 Duriron Co Pumps
US4335997A (en) * 1980-01-16 1982-06-22 General Motors Corporation Stress resistant hybrid radial turbine wheel
US4659288A (en) * 1984-12-10 1987-04-21 The Garrett Corporation Dual alloy radial turbine rotor with hub material exposed in saddle regions of blade ring
JP3679875B2 (ja) * 1996-10-31 2005-08-03 三菱重工業株式会社 ラジアルタービン羽根車
JP3462870B2 (ja) 2002-01-04 2003-11-05 三菱重工業株式会社 ラジアルタービン用羽根車

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Title
See references of WO2006114007A1 *

Also Published As

Publication number Publication date
WO2006114007A1 (fr) 2006-11-02
KR101184952B1 (ko) 2012-10-02
CN101166890B (zh) 2011-12-14
CN101166890A (zh) 2008-04-23
JP4718599B2 (ja) 2011-07-06
US7771170B2 (en) 2010-08-10
KR20080002882A (ko) 2008-01-04
JP2008539356A (ja) 2008-11-13
EP1717414A1 (fr) 2006-11-02
RU2007143991A (ru) 2009-06-10
DE502006002383D1 (de) 2009-01-29
US20080063528A1 (en) 2008-03-13
EP1875045B1 (fr) 2008-12-17

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