WO2006122438A1 - Couronne directrice - Google Patents

Couronne directrice Download PDF

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Publication number
WO2006122438A1
WO2006122438A1 PCT/CH2006/000248 CH2006000248W WO2006122438A1 WO 2006122438 A1 WO2006122438 A1 WO 2006122438A1 CH 2006000248 W CH2006000248 W CH 2006000248W WO 2006122438 A1 WO2006122438 A1 WO 2006122438A1
Authority
WO
WIPO (PCT)
Prior art keywords
ring
outer ring
nozzle ring
nozzle
slots
Prior art date
Application number
PCT/CH2006/000248
Other languages
German (de)
English (en)
Inventor
Markus Loos
Balz Flury
Marcel Zehnder
Bent Phillipsen
Peter Schellenberg
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
Publication of WO2006122438A1 publication Critical patent/WO2006122438A1/fr

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • 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
    • F05D2240/55—Seals

Definitions

  • the invention relates to the field of exhaust gas turbochargers for internal combustion engines.
  • the invention relates to a nozzle ring according to the preamble of patent claim 1, which directs the working fluid to the blades of the turbine of the exhaust gas turbocharger.
  • exhaust gas turbochargers to increase the performance of internal combustion engines
  • the exhaust gas turbine of the turbocharger is charged with the exhaust gases of the internal combustion engine and their kinetic energy used for sucking and compressing air for the internal combustion engine.
  • a nozzle ring is arranged coaxially to the shaft of the turbine, which directs the exhaust gases to the blades of the turbine.
  • sooner or later contamination of the rotor blades and the nozzle ring will occur in the exhaust gas turbine, the latter being considerably more affected.
  • heavy oil operation forms a hard dirt layer on the nozzle ring.
  • Object of the present invention is therefore to provide a nozzle ring of the type mentioned, which withstands the large thermal loads without negatively affecting the efficiency of the exhaust gas turbocharger.
  • the openings, which are necessary for the elastic movability of the guide vanes of the nozzle ring are closed by covers in the parts carrying the guide vanes. As a result, it can be prevented that exhaust gas flows through the housing during operation and thus energy is lost unused. Further advantages emerge from the dependent claims.
  • FIG. 1 is a schematic representation of a first embodiment of an inventive nozzle ring with a shortened outer ring and a cover
  • FIG. 2 is a schematic representation of a second embodiment of a nozzle ring according to the invention with a cover ring
  • FIG. 3 shows a detailed view of a third embodiment of the inventive nozzle ring in the normal state
  • FIG. 4 shows a detailed view of the embodiment of the inventive nozzle ring according to FIG. 3 under thermal stress.
  • Fig. 1 shows schematically a part of an exhaust gas turbine.
  • a blade carrier 12 On a blade carrier 12, a plurality of turbine blades 11 are arranged.
  • the exhaust gas guided by an internal combustion engine onto the turbine is guided through a flow channel via the guide vanes 23 of a nozzle ring onto the rotor blades.
  • the flow channel is limited by turbine housing parts 42 and, in the region of the nozzle ring, by an inner ring 21 and an outer ring 22 of the nozzle ring.
  • the vanes 23 are distributed along the circumference and arranged between the inner ring and outer ring and connected thereto. They can be made in one piece with inner ring and outer ring or be composed.
  • the outer ring is shorter in the axial direction than the guide vanes 23.
  • the guide vanes project beyond the outer ring. This allows an elastic forming the guide vane due to thermal stress, such as may occur during a washing with cold water.
  • the particularly thin trained in the outflow region, heated by the hot exhaust gas flow guide blade is cooled in shock like a shock and contracts it. Thanks to the free, unattached outer end, the guide vane survives this load without permanent deformation.
  • a cover 3 is arranged radially outside the free end of the guide blade.
  • the cover can be firmly connected to the outer ring, as long as the deformability of the guide vane in the outflow region is not impaired by the connection.
  • the cover may be mounted on the vanes during installation with a slight interference fit without compromising the aforementioned ductility.
  • the axial length of the cover is advantageously in the range between about one third of the blade length to a blade length. This ensures a sufficiently large freedom of movement of the guide vane.
  • the inner ring can be designed correspondingly shortened and the cover in the region of the inner ring to be arranged radially against the inside.
  • a slot 24 is embedded in the outer ring 22 between two guide vanes 23 of the nozzle ring. If the guide vanes are subjected to a high level of thermal stress, they can deform independently of each other and elastically from the outer ring thanks to these slots. In order to prevent the bypass flow through these slots during operation, the slots are closed according to the invention with a cover ring 3. The cover ring is pushed radially outwards onto the outer ring and thus does not impair the freedom of movement of the guide vane and the part of the outer ring connected to the vane.
  • the cover ring can be made of fiberglass or carbon fiber mats.
  • the cover ring may be formed as an open ring (snap ring). As a result, it can be firmly fixed to the outer ring of the nozzle ring and, in addition, permits a certain expansion of the outer ring radially outwards.
  • the cover ring itself may also have slots, which, however, do not come to rest over the slots in the outer ring, so as not to interfere with the sealing of the flow channel against the turbine housing.
  • compensating bends may be provided in the cover ring, which permit a controlled stretching of the cover ring without material overloading.
  • the slots can also be closed individually with a plastic plate or a metal sheet or stuffed with a ceramic or metallic filler. It is important again that the freedom of movement of the vane is not affected. However, this is ensured as long as the sheet or the filling compound are designed to be more elastic than the thermally stressed parts of the nozzle ring.
  • the inner ring formed corresponding slotted and the cover ring in the region of the inner ring can be arranged radially aligned against the inside.
  • FIGS. 3 and 4 A third embodiment, slightly modified from the second embodiment, is shown in FIGS. 3 and 4.
  • Fig. 3 shows a section through a slot in the outer ring 22.
  • the slot is not guided by the entire radial thickness Di of the outer ring, but only as a recess to a residual thickness D 2nd In this way, a thin outer ring 3 remains between the individual, separated by the slots 24 segments of the outer ring.
  • the thinned wall as shown in FIG. 4, can be compressed or stretched better under thermal load than the wall of the outer ring in full strength.
  • the residual thickness D 2 is advantageously in the region of the guide vane thickness in the outflow region or below. This ensures that in extreme cases, not the guide blade breaks, but the wall of the outer ring, which lies radially outside the flow.
  • a fourth embodiment provides that in the outer ring of the nozzle ring, a recess is provided, which is guided along the contour of the guide vane.
  • the recess can in turn be designed as a slit to a residual thickness, or be formed over a large area in the entire area in and around the contour of the guide blade as a sink with a reduced wall thickness.
  • Also in the third and fourth embodiments may be formed instead of the outer ring of the inner ring with the corresponding slot cover against radially inward.
  • Such a design as a snap ring has no great influence on the strength of the nozzle ring, but helps to reduce certain voltages.

Landscapes

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

Abstract

L'invention concerne une couronne directrice dotée d'orifices (24) nécessaires au mouvement élastique des aubes directrices (23). Ces orifices, dans lesquels se trouvent les éléments (22) portant les aubes directrices, sont fermés par des couvercles (3). Ceci permet d'éviter que des gaz d'échappement ne s'écoulent par le carter lorsque l'organe fonctionne et, par voie de conséquence, une perte d'énergie non utilisée.
PCT/CH2006/000248 2005-05-20 2006-05-08 Couronne directrice WO2006122438A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP05405356A EP1724443A1 (fr) 2005-05-20 2005-05-20 Couronne directrice
EP05405356.6 2005-05-20

Publications (1)

Publication Number Publication Date
WO2006122438A1 true WO2006122438A1 (fr) 2006-11-23

Family

ID=35063260

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CH2006/000248 WO2006122438A1 (fr) 2005-05-20 2006-05-08 Couronne directrice

Country Status (2)

Country Link
EP (1) EP1724443A1 (fr)
WO (1) WO2006122438A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2945331B1 (fr) * 2009-05-07 2011-07-22 Snecma Virole pour stator de turbomoteur d'aeronef a fentes de dechargement mecanique d'aubes.
CZ305366B6 (cs) * 2011-03-31 2015-08-19 Vlastimil Sedláček Způsob montáže statorových lopatek turbíny a jejich zajištění pomocí bandáže a zařízení k provádění tohoto způsobu
DE102019103640A1 (de) 2019-02-13 2020-08-13 Mitsubishi Hitachi Power Systems Europe Gmbh Brennstoffdüse mit Dehnungsschlitzen für einen Kohlenstaubbrenner

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2447942A (en) * 1944-12-05 1948-08-24 Rateau Soc Turbine distributor and nozzle
US3824034A (en) * 1971-05-03 1974-07-16 Mtu Friedrichshafen Gmbh Guide blade ring
EP0781897B1 (fr) * 1995-12-29 2001-05-23 ABB Turbo Systems AG Méthode et dispositif pour le nettoyage humide des anneaux de tuyères de turbocompresseur
WO2004044387A1 (fr) * 2002-11-13 2004-05-27 Abb Turbo Systems Ag Aube directrice a fente
DE10327977A1 (de) * 2003-06-21 2005-01-05 Alstom Technology Ltd Seitenwandgestaltung eines umlenkenden Strömungskanals

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2447942A (en) * 1944-12-05 1948-08-24 Rateau Soc Turbine distributor and nozzle
US3824034A (en) * 1971-05-03 1974-07-16 Mtu Friedrichshafen Gmbh Guide blade ring
EP0781897B1 (fr) * 1995-12-29 2001-05-23 ABB Turbo Systems AG Méthode et dispositif pour le nettoyage humide des anneaux de tuyères de turbocompresseur
WO2004044387A1 (fr) * 2002-11-13 2004-05-27 Abb Turbo Systems Ag Aube directrice a fente
DE10327977A1 (de) * 2003-06-21 2005-01-05 Alstom Technology Ltd Seitenwandgestaltung eines umlenkenden Strömungskanals

Also Published As

Publication number Publication date
EP1724443A1 (fr) 2006-11-22

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