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WO2005119030A1 - Refroidissement de moyeu de turbine a gaz d'echappement - Google Patents

Refroidissement de moyeu de turbine a gaz d'echappement Download PDF

Info

Publication number
WO2005119030A1
WO2005119030A1 PCT/CH2004/000341 CH2004000341W WO2005119030A1 WO 2005119030 A1 WO2005119030 A1 WO 2005119030A1 CH 2004000341 W CH2004000341 W CH 2004000341W WO 2005119030 A1 WO2005119030 A1 WO 2005119030A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
hub
housing
turbine wheel
cooling
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/CH2004/000341
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 PCT/CH2004/000341 priority Critical patent/WO2005119030A1/fr
Publication of WO2005119030A1 publication Critical patent/WO2005119030A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • 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
    • F01D5/046—Heating, heat insulation or cooling 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

Definitions

  • the invention relates to the field of exhaust gas turbochargers. It relates to an exhaust gas turbine according to the preamble of patent claim 1.
  • Exhaust gas turbochargers are used to increase the performance of fuel engines.
  • the exhaust gas turbochargers are operated at ever higher speeds.
  • the turbines of the exhaust gas turbocharger are loaded to the current state.
  • the expected service life of the turbine calculated as the time span from the stress to the failure of the turbine, depends mainly on two parameters, the aterial temperature of the turbine wheel and the speed, or the peripheral speed.
  • the blades in the hot entry area of the turbine wheel are particularly loaded. In order to cope with the increased load, the blades have to be built more solidly. However, if the blades are reinforced to achieve higher speeds under creep stress, this has a disadvantageous effect on the bursting behavior. The blades do not separate from the hub and the hub bursts.
  • the invention has for its object to provide a turbine in which the blades of the turbine wheel separate from the hub during natural bursting and which can still be operated at high speeds. According to the invention, this object is achieved with a turbine having the features of patent claim 1.
  • the turbine according to the invention has a cooled turbine wheel.
  • the hub of the turbine wheel is cooled via a cooling duct arranged in the adjacent turbine housing.
  • the resulting lower material temperatures in the turbine wheel allow high speeds when the creep load is applied without the need to thicken the blades.
  • the thin blades disengage from the hub during natural bursting.
  • the cooling of the turbine wheel according to the invention in combination with the thin blades at the same time guarantees high application limits and low manufacturing costs through reduced burst protection measures on the turbine housing.
  • the housing wall between the cooling channel and the turbine hub rear wall can contain a material with improved thermal conductivity.
  • this heat-conducting housing wall can have a surface-enlarging structure, both in the interior of the cooling channel and in relation to the rear wall of the turbine hub.
  • the rear wall of the turbine hub can also be provided with a corresponding surface-enlarging structure in order to improve the heat transfer. Further advantages result from the dependent claims.
  • FIG. 1 is a schematic sectional view of a turbine according to the invention with a cooling chamber
  • FIG. 2 shows a schematic sectional illustration of the turbine according to the invention with a cooling chamber wall with a surface-enlarging structure
  • FIG 3 shows a schematic sectional illustration of the turbine according to the invention with a cooling chamber wall and a turbine wheel hub rear wall with a surface-enlarging structure.
  • FIG. 1 schematically shows the turbine according to the invention.
  • Turbine housing 21, 22, a rotatable turbine wheel is arranged.
  • the turbine wheel comprises a hub 11 and several arranged on the front of the hub; Blades 15 and is connected via a shaft 30 to the compressor wheel, not shown.
  • the turbine housing with the gas inlet side housing part 22 to the left of the turbine wheel and the gas outlet side housing part 21 forms, together with the hub of the turbine wheel, a flow channel 40, in which hot exhaust gases flow through during operation of the exhaust gas turbocharger (see large arrow).
  • the turbine can be designed as a pure radial turbine, with a radial inflow and axial exit of the exhaust gases, or, as shown in FIG. 2, as a so-called mixed flow turbine with an inflow with radial and axial components and an axial exit.
  • a cooling duct 50 is embedded in the back of the hub of the turbine wheel, in the housing 22 on the gas inlet side.
  • the cooling channel extends radially along the hub of the turbine wheel in order to enable it to be optimally cooled.
  • the hub of the turbine wheel is drawn up radially on its rear side 12 up to the gas inlet edges 16 of the rotor blades, as a result of which the heat can be taken directly from the area with the greatest thermal load.
  • the blades are cooled via the hub and can be made less solid thanks to the lower thermal load. Without cooling, the blades would have to be much stronger in the area of the hub attachment, which would make it impossible to detach the blades from the hub in the event of a burst.
  • the hub In the circumferential direction between the blades, the hub can be used to save weight and reduce the moment of inertia with a radial after provided on the inside directed arch edge, and so be guided a little less radially outwards.
  • a heat-transmitting housing wall 23 is arranged between the cooling duct 50 and the rear 12 of the hub of the turbine wheel.
  • the heat from the hub of the turbine wheel is extracted according to the invention through the rear wall 12 of the hub of the turbine wheel and through the heat-transferring housing wall 23 and dissipated to a heat exchanger via a cooling medium, for example cooling water or oil.
  • the heat-transmitting housing wall can contain a material that has an improved thermal conductivity.
  • it can be treated with a subsequently applied material in the corresponding housing wall or made entirely of another material as an independent housing part and connected to the rest of the turbine housing in a positive or non-positive manner.
  • FIG. 2 Another measure is shown in FIG. 2.
  • the corresponding inside of the heat transferring housing wall 24 is provided with a surface-enlarging structure.
  • several fins are provided, which are washed by the cooling medium.
  • Other surface-enlarging structures would also be possible, for example porous material through which the cooling medium flows, or several small cooling channels in the housing wall.
  • the surface rear wall 13 of the hub of the turbine wheel and the opposite heat-transmitting housing wall 25 can also be provided with a surface-enlarged structure according to FIG. 3. More heat can be transported via the enlarged surface, which improves the overall heat flow, indicated by the small arrows.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

L'invention concerne une turbine présentant une roue refroidie. Selon l'invention, le moyeu (11) de la roue est refroidi par l'intermédiaire d'un canal de refroidissement (50) situé dans le carter adjacent (22). Les matériaux de la roue de turbine présentant ainsi des températures plus basses, il est possible d'obtenir des vitesses de rotation élevées dans des conditions de fluage, sans devoir nécessairement augmenter l'épaisseur des pales. Les fines pales se détachent du moyeu lors d'un l'éclatement naturel.
PCT/CH2004/000341 2004-06-04 2004-06-04 Refroidissement de moyeu de turbine a gaz d'echappement Ceased WO2005119030A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CH2004/000341 WO2005119030A1 (fr) 2004-06-04 2004-06-04 Refroidissement de moyeu de turbine a gaz d'echappement

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CH2004/000341 WO2005119030A1 (fr) 2004-06-04 2004-06-04 Refroidissement de moyeu de turbine a gaz d'echappement

Publications (1)

Publication Number Publication Date
WO2005119030A1 true WO2005119030A1 (fr) 2005-12-15

Family

ID=34957572

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CH2004/000341 Ceased WO2005119030A1 (fr) 2004-06-04 2004-06-04 Refroidissement de moyeu de turbine a gaz d'echappement

Country Status (1)

Country Link
WO (1) WO2005119030A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011116658A1 (de) * 2011-10-21 2013-04-25 Daimler Ag Abgasturbolader für eine Verbrennungskraftmaschine und Verfahren zum Betrieb eines Abgasturboladers
WO2014198453A1 (fr) * 2013-06-13 2014-12-18 Continental Automotive Gmbh Turbocompresseur à gaz d'échappement avec roue de turbine radiale-axiale
US11002154B2 (en) 2017-03-30 2021-05-11 Vitesco Technologies GmbH Turbocharger for an internal combustion engine, and turbine housing

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB645258A (en) * 1946-05-10 1950-10-25 Alfred Buechi Improvements in or relating to turbines
US4107927A (en) * 1976-11-29 1978-08-22 Caterpillar Tractor Co. Ebullient cooled turbocharger bearing housing
DE3322436A1 (de) * 1983-06-22 1985-01-03 Volkswagenwerk Ag, 3180 Wolfsburg Abgasturbolader mit einen scheibenfoermigen luftspalt aufweisender trennwand zwischen ladeluftkompressor und abgasturbine
US6739845B2 (en) * 2002-05-30 2004-05-25 William E. Woollenweber Compact turbocharger

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB645258A (en) * 1946-05-10 1950-10-25 Alfred Buechi Improvements in or relating to turbines
US4107927A (en) * 1976-11-29 1978-08-22 Caterpillar Tractor Co. Ebullient cooled turbocharger bearing housing
DE3322436A1 (de) * 1983-06-22 1985-01-03 Volkswagenwerk Ag, 3180 Wolfsburg Abgasturbolader mit einen scheibenfoermigen luftspalt aufweisender trennwand zwischen ladeluftkompressor und abgasturbine
US6739845B2 (en) * 2002-05-30 2004-05-25 William E. Woollenweber Compact turbocharger

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011116658A1 (de) * 2011-10-21 2013-04-25 Daimler Ag Abgasturbolader für eine Verbrennungskraftmaschine und Verfahren zum Betrieb eines Abgasturboladers
WO2014198453A1 (fr) * 2013-06-13 2014-12-18 Continental Automotive Gmbh Turbocompresseur à gaz d'échappement avec roue de turbine radiale-axiale
KR101823744B1 (ko) * 2013-06-13 2018-01-30 콘티넨탈 오토모티브 게엠베하 방사방향/축방향 터빈 휠을 갖는 터보차저
US10190415B2 (en) 2013-06-13 2019-01-29 Continental Automotive Gmbh Turbocharger with a radial-axial turbine wheel
US11002154B2 (en) 2017-03-30 2021-05-11 Vitesco Technologies GmbH Turbocharger for an internal combustion engine, and turbine housing

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