EP1890011A1 - Turbine axiale avec virole rainurée - Google Patents

Turbine axiale avec virole rainurée Download PDF

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Publication number
EP1890011A1
EP1890011A1 EP06405335A EP06405335A EP1890011A1 EP 1890011 A1 EP1890011 A1 EP 1890011A1 EP 06405335 A EP06405335 A EP 06405335A EP 06405335 A EP06405335 A EP 06405335A EP 1890011 A1 EP1890011 A1 EP 1890011A1
Authority
EP
European Patent Office
Prior art keywords
turbine
ring
blades
segments
exhaust gas
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Withdrawn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
EP06405335A
Other languages
German (de)
English (en)
Inventor
Josef Bättig
Karl-Heinz Rohne
Matthias Richner
William Gizzi
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 EP06405335A priority Critical patent/EP1890011A1/fr
Priority to PCT/EP2007/058202 priority patent/WO2008017681A1/fr
Publication of EP1890011A1 publication Critical patent/EP1890011A1/fr
Withdrawn legal-status Critical Current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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • F01D25/002—Cleaning of turbomachines
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous

Definitions

  • the invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines.
  • the axial turbine comprises a turbine wheel with blades and a cover ring radially surrounding the blades.
  • Exhaust gas turbochargers are used to increase the performance of internal combustion engines, in particular reciprocating engines.
  • an exhaust gas turbocharger usually has a centrifugal compressor and a radial or axial turbine. From a certain size it makes sense to use axial turbines for the drive of the compressor. So that the exhaust gas can not bypass the blades of the axial turbine, they are surrounded by a housing part radially outward. This housing part thus limits the flow channel radially outward in the region of the rotor blades.
  • This housing part may be formed as an integral part of a diffuser arranged downstream of the rotor blades, as an integral part of a radially outer housing wall of a nozzle ring arranged upstream of the rotor blades, or as a separate cover ring.
  • the exhaust gas is heavily contaminated with soot, ash and other pollutants. These are deposited over time on certain components of the exhaust gas turbine, in particular on the blades, the cover ring, the guide vanes of the nozzle ring and the diffuser, and reduce the efficiency of the exhaust gas turbine, which reduces the overall performance of the internal combustion engine. For this reason, the soiled components of the exhaust gas turbine must be cleaned at regular intervals. Usually, the Exhaust gas turbine washed with water. To minimize the burden on the contaminated components, turbocharger manufacturers dictate that the load on the internal combustion engine be reduced during the wash cycle. As a result, the temperature of the affected components is already slightly reduced before the washing process, resulting in smaller loads.
  • CH 35 11 42 discloses an axial turbine having a turbine wheel with blades and a cover ring radially surrounding the blades, wherein the cover ring is divided into a plurality of separate segments.
  • the object of the present invention is to improve the exhaust gas turbine of an exhaust gas turbocharger such that it also withstands cleaning operations under full load without signs of wear on the components of the exhaust gas turbine.
  • the cover ring is radially divided outside the rotor blades of the turbine wheel through slots in a plurality of annular segments which are separated from one another in the circumferential direction.
  • the segments according to the invention are connected via thin ribs to a circumferential ring, which is not influenced by the washing process.
  • the cover ring loses its tangential relationship as a ring.
  • the cover pulls in a sudden cooling, as occurs during cleaning of the exhaust gas turbine, no longer together in the radial direction.
  • this means that the cover ring maintains the diameter of the hot state during the cleaning process and only the slots between the individual segments are larger.
  • a strip of the rotor blades of the turbine wheel can be prevented at the housing parts arranged radially outside.
  • the segments are connected in both axial directions via ribs, each with a circumferential ring.
  • the effect of the expanding slots can be enhanced with rapid cooling, since no temperature gradient in the axial direction results in the area radially outside the blades of the turbine wheel during the cleaning process.
  • the slots are advantageously as small as possible, ie in the microscopic range formed.
  • Fig. 1 shows a section through the axis of an axial turbine of an exhaust gas turbocharger according to the prior art.
  • the turbine wheel 10 rotatably mounted in a housing includes a hub 11 and a plurality of blades 12 disposed thereon.
  • the exhaust flow needed to drive the turbine is transmitted through a flow channel from the gas inlet housing 42 via the nozzle ring 20 to the blades of the turbine wheel and further through the diffuser 31 led to the gas outlet housing 41.
  • the nozzle ring 20 comprises an inner wall 21 and an outer wall 22 and vanes 23 arranged therebetween.
  • the walls of the nozzle ring as well as the diffuser are housing parts which delimit the flow channel of the exhaust gas.
  • the flow channel in the region of the rotor blades is delimited by a cover ring radially enclosing the rotor blades.
  • This housing part can, as in FIG. 1, be formed as an integral part of the diffuser 31 arranged downstream of the rotor blades.
  • the cover ring may be formed as an integral part of the radially outer housing wall 22 of the nozzle ring or as an independent component.
  • FIG. 2 shows a section through the axis of an axial turbine of an exhaust-gas turbocharger with a cover ring 5 designed according to the invention, which delimits the flow channel in the area radially outside the rotor blades 12 of the turbine wheel.
  • the cover ring is shown enlarged in Fig. 3 again.
  • the cover ring comprises a plurality of segments 51 which are separated from one another by slits 57 along the circumference and at least one circumferential one Ring 54 and 55, respectively.
  • the segments are arranged directly radially outside the rotor blades. In this area, the cover ring thus loses its tangential relationship.
  • the cover ring therefore does not contract even in the case of a sudden cooling in the radial direction. Only the slots 57 between the individual segments are larger. As a result, a strip of the turbine can be prevented.
  • the segments 51 are connected via ribs 52 and 53, respectively, to the encircling rings 54 and 55, respectively.
  • the cover ring 5 is advantageously fastened to the diffuser 31 or the gas outlet housing 41, or, as indicated in FIG. 2, clamped between the two parts.
  • the cover ring can be screwed tightly by means of fastening holes 6 arranged in the holes 56.
  • the peripheral rings are advantageously separated by at least one housing part of the flow channel in the region of the blades, so that no cold water can reach the rings during the cleaning process. Thus, the rings undergo no cooling during the cleaning of the exhaust gas turbine and thus do not contract thermally.
  • FIG. 4 shows a first embodiment of the cover ring 5 according to the invention with a ring 55 arranged on the outlet side, on which the segments 51 are fastened in each case via ribs 53.
  • FIG. 5 shows a second embodiment of the cover ring 5 according to the invention with a ring 54 arranged on the inlet side and an outlet-side ring 55 on which the segments 51 are respectively fastened via ribs 52 and 53.
  • the rings 54 and 55 are set back with respect to the radially inner surface of the segments in the radial direction, so that they do not come in the installed state directly in contact with the flow or the cleaning liquid.
  • the ribs 52 and 53 are made as thin as possible to the heat conduction or temperature compensation between the segments 51 and the rings 54, respectively. 55 to minimize the washing.
  • the slots 57 between the individual segments 51 are formed as thin as possible. Since the temperature of the segments in operation is likely to be higher than the temperature during manufacture, the slots formed during manufacture close during operation due to the expansion of the segments along the circumference.
  • the slot width should, at least during operation of the exhaust gas turbine, be in the microscopic range of a few micrometers.
  • the inventive exhaust gas turbine can be used instead of driving a compressor as a power turbine, about to drive an electric generator or a mechanical machine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP06405335A 2006-08-07 2006-08-07 Turbine axiale avec virole rainurée Withdrawn EP1890011A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06405335A EP1890011A1 (fr) 2006-08-07 2006-08-07 Turbine axiale avec virole rainurée
PCT/EP2007/058202 WO2008017681A1 (fr) 2006-08-07 2007-08-07 Turbine axiale comprenant une bague de recouvrement fendue

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06405335A EP1890011A1 (fr) 2006-08-07 2006-08-07 Turbine axiale avec virole rainurée

Publications (1)

Publication Number Publication Date
EP1890011A1 true EP1890011A1 (fr) 2008-02-20

Family

ID=37622331

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06405335A Withdrawn EP1890011A1 (fr) 2006-08-07 2006-08-07 Turbine axiale avec virole rainurée

Country Status (2)

Country Link
EP (1) EP1890011A1 (fr)
WO (1) WO2008017681A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009045167A1 (de) 2009-09-30 2011-04-07 Man Diesel & Turbo Se Turbine eines Abgasturbolader

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB869908A (en) * 1958-03-25 1961-06-07 Zd Y V I Plzen A packing device for the rotor blades of turbines
US3286459A (en) * 1963-12-31 1966-11-22 Gen Motors Corp Turbine inlet screen assembly
US3730640A (en) * 1971-06-28 1973-05-01 United Aircraft Corp Seal ring for gas turbine
DE2820189A1 (de) * 1978-05-09 1979-11-22 Teves Gmbh Alfred Trommelbremse
GB2076067A (en) * 1980-05-16 1981-11-25 Mtu Muenchen Gmbh Axial-flow compressor or turbine outer casing
JPH05288080A (ja) * 1992-04-10 1993-11-02 Yanmar Diesel Engine Co Ltd ガスタービンエンジン
US5593276A (en) * 1995-06-06 1997-01-14 General Electric Company Turbine shroud hanger
EP1475515A2 (fr) * 2003-05-06 2004-11-10 General Electric Company Dispositif de réglage du jeu des extrémités des aubes d'une turbine à gaz
EP1580404A2 (fr) * 2004-03-26 2005-09-28 Rolls-Royce Deutschland Ltd & Co KG Ensemble pour le réglage autoajustable du jeu des aubes dans une turbine à deux ou multiples étages

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6896483B2 (en) * 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
US6877952B2 (en) * 2002-09-09 2005-04-12 Florida Turbine Technologies, Inc Passive clearance control

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB869908A (en) * 1958-03-25 1961-06-07 Zd Y V I Plzen A packing device for the rotor blades of turbines
US3286459A (en) * 1963-12-31 1966-11-22 Gen Motors Corp Turbine inlet screen assembly
US3730640A (en) * 1971-06-28 1973-05-01 United Aircraft Corp Seal ring for gas turbine
DE2820189A1 (de) * 1978-05-09 1979-11-22 Teves Gmbh Alfred Trommelbremse
GB2076067A (en) * 1980-05-16 1981-11-25 Mtu Muenchen Gmbh Axial-flow compressor or turbine outer casing
JPH05288080A (ja) * 1992-04-10 1993-11-02 Yanmar Diesel Engine Co Ltd ガスタービンエンジン
US5593276A (en) * 1995-06-06 1997-01-14 General Electric Company Turbine shroud hanger
EP1475515A2 (fr) * 2003-05-06 2004-11-10 General Electric Company Dispositif de réglage du jeu des extrémités des aubes d'une turbine à gaz
EP1580404A2 (fr) * 2004-03-26 2005-09-28 Rolls-Royce Deutschland Ltd & Co KG Ensemble pour le réglage autoajustable du jeu des aubes dans une turbine à deux ou multiples étages

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009045167A1 (de) 2009-09-30 2011-04-07 Man Diesel & Turbo Se Turbine eines Abgasturbolader

Also Published As

Publication number Publication date
WO2008017681A1 (fr) 2008-02-14

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