EP1717414A1 - Roue de turbine - Google Patents

Roue de turbine Download PDF

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Publication number
EP1717414A1
EP1717414A1 EP05405319A EP05405319A EP1717414A1 EP 1717414 A1 EP1717414 A1 EP 1717414A1 EP 05405319 A EP05405319 A EP 05405319A EP 05405319 A EP05405319 A EP 05405319A EP 1717414 A1 EP1717414 A1 EP 1717414A1
Authority
EP
European Patent Office
Prior art keywords
hub
blade
scalloping
turbine wheel
contour
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.)
Withdrawn
Application number
EP05405319A
Other languages
German (de)
English (en)
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 EP05405319A priority Critical patent/EP1717414A1/fr
Priority to DE502006002383T priority patent/DE502006002383D1/de
Priority to PCT/CH2006/000176 priority patent/WO2006114007A1/fr
Priority to KR1020077024696A priority patent/KR101184952B1/ko
Priority to RU2007143991/06A priority patent/RU2007143991A/ru
Priority to CN200680014115XA priority patent/CN101166890B/zh
Priority to JP2008508044A priority patent/JP4718599B2/ja
Priority to EP06705416A priority patent/EP1875045B1/fr
Publication of EP1717414A1 publication Critical patent/EP1717414A1/fr
Priority to US11/976,708 priority patent/US7771170B2/en
Withdrawn legal-status Critical Current

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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
    • F01D5/04—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
    • F01D5/04—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
    • 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 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 may 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 the exhaust gas inlet edge of adjacent blades to a continuously extending scalloping contour.
  • scalloping contour such as in FIG EP 1 462 607 A1 shown, take an asymmetrical course between the exhaust gas inlet edges of adjacent blades.
  • the blades are formed three-dimensional 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 by the strong centrifugal forces pulled radially outwards.
  • 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 region of the scalloping contour, in particular at the lowest point, which can be life-limiting for the turbine wheel.
  • 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 of the rear wall of the shaft hub limited by the scalloping contour into two equally sized partial surfaces. The load of the two partial surfaces with respect to Deformation during operation is thereby aligned and the unilateral maximum load is reduced.
  • 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 area of attachment results in an intersection curve between the blade contour and the hub surface.
  • 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.
  • FIG. 2 This rotation can also be clearly seen in the representation of the turbine wheel according to the prior art from FIG. 2 and illustrated with an arrow.
  • the figure shows a turbine wheel under load, so that caused by the centrifugal forces 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 F 1 and F 2 are aligned with one another.
  • 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)
EP05405319A 2005-04-27 2005-04-27 Roue de turbine Withdrawn EP1717414A1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP05405319A EP1717414A1 (fr) 2005-04-27 2005-04-27 Roue de turbine
DE502006002383T DE502006002383D1 (de) 2005-04-27 2006-03-24 Turbinenrad
PCT/CH2006/000176 WO2006114007A1 (fr) 2005-04-27 2006-03-24 Roue de turbine
KR1020077024696A KR101184952B1 (ko) 2005-04-27 2006-03-24 터빈 휠
RU2007143991/06A RU2007143991A (ru) 2005-04-27 2006-03-24 Турбинное колесо
CN200680014115XA CN101166890B (zh) 2005-04-27 2006-03-24 涡轮
JP2008508044A JP4718599B2 (ja) 2005-04-27 2006-03-24 タービン・ホイール
EP06705416A EP1875045B1 (fr) 2005-04-27 2006-03-24 Roue de turbine
US11/976,708 US7771170B2 (en) 2005-04-27 2007-10-26 Turbine wheel

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP1717414A1 true EP1717414A1 (fr) 2006-11-02

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 After (1)

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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
JPH10131704A (ja) * 1996-10-31 1998-05-19 Mitsubishi Heavy Ind Ltd ラジアルタービン羽根車
EP1462607A1 (fr) * 2002-01-04 2004-09-29 Mitsubishi Heavy Industries, Ltd. Roue a aubes pour turbine radiale

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
JPH10131704A (ja) * 1996-10-31 1998-05-19 Mitsubishi Heavy Ind Ltd ラジアルタービン羽根車
EP1462607A1 (fr) * 2002-01-04 2004-09-29 Mitsubishi Heavy Industries, Ltd. Roue a aubes pour turbine radiale

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1998, no. 10 31 August 1998 (1998-08-31) *

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
EP1875045A1 (fr) 2008-01-09
RU2007143991A (ru) 2009-06-10
DE502006002383D1 (de) 2009-01-29
US20080063528A1 (en) 2008-03-13
EP1875045B1 (fr) 2008-12-17

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