EP1724443A1 - Couronne directrice - Google Patents

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Publication number
EP1724443A1
EP1724443A1 EP05405356A EP05405356A EP1724443A1 EP 1724443 A1 EP1724443 A1 EP 1724443A1 EP 05405356 A EP05405356 A EP 05405356A EP 05405356 A EP05405356 A EP 05405356A EP 1724443 A1 EP1724443 A1 EP 1724443A1
Authority
EP
European Patent Office
Prior art keywords
ring
outer ring
nozzle
nozzle ring
slots
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Withdrawn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
EP05405356A
Other languages
German (de)
English (en)
Inventor
Markus Loos
Balz Flury
Marcel Zehnder
Bent Phillipsen
Peter Schellenberg
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 EP05405356A priority Critical patent/EP1724443A1/fr
Priority to PCT/CH2006/000248 priority patent/WO2006122438A1/fr
Publication of EP1724443A1 publication Critical patent/EP1724443A1/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Withdrawn legal-status Critical Current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
    • 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 of 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.
  • An apparatus and a method for wet cleaning of the nozzle ring of an exhaust gas turbocharger turbine is in EP 0 781 897 B1 described.
  • a special design of the gas inlet housing allows the injection of water in the area immediately before the nozzle ring.
  • the relatively cold water is carried along after injection into the exhaust gas stream of the internal combustion engine from this to the nozzle ring. There it encounters the dirt deposits of the nozzle ring, which are suddenly very strongly cooled by the evaporation of the water on the surface. The water penetrates into the dirt layer and the deposits are partially dissolved. Applying this thermal shock treatment several times will result in a clean 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.
  • 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 to the turbine is guided through a flow channel via the guide vanes 23 of a nozzle ring on the 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 for elastic deformation the vane due to thermal stress, such as may occur during a cold water wash.
  • 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, unpaved outer end of 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 arranged the cover in the region of the inner ring radially against the inside.
  • a slot 24 is embedded in the outer ring 22 between two guide vanes 23 of the nozzle ring. At high thermal load of the guide vanes, these can deform independently of each other and elastically from the outer ring thanks to these slots.
  • 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 Andeckring can be made of glass fiber 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 allow 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 filling compound. 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 correspondingly slotted and the cover ring may be arranged in the region of the inner ring 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 through the entire radial thickness D 1 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 can, as shown in FIG. 4, compress or stretch better under thermal stress 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 a recess is provided in the outer ring of the nozzle ring, 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.
  • 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.
EP05405356A 2005-05-20 2005-05-20 Couronne directrice Withdrawn EP1724443A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP05405356A EP1724443A1 (fr) 2005-05-20 2005-05-20 Couronne directrice
PCT/CH2006/000248 WO2006122438A1 (fr) 2005-05-20 2006-05-08 Couronne directrice

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP1724443A1 true EP1724443A1 (fr) 2006-11-22

Family

ID=35063260

Family Applications (1)

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

Country Status (2)

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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010128025A1 (fr) * 2009-05-07 2010-11-11 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

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010128025A1 (fr) * 2009-05-07 2010-11-11 Snecma Virole pour stator de turbomoteur d'aeronef a fentes de dechargement mecanique d'aubes
FR2945331A1 (fr) * 2009-05-07 2010-11-12 Snecma Virole pour stator de turbomoteur d'aeronef a fentes de dechargement mecanique d'aubes.
CN102422027A (zh) * 2009-05-07 2012-04-18 斯奈克玛 用于带有机械叶片载荷转移裂隙的航空器涡轮发动机定子的壳体
RU2527809C2 (ru) * 2009-05-07 2014-09-10 Снекма Турбинный двигатель летательного аппарата, его модуль, часть статора для такого модуля, а также кольцо для такого статора
US9017022B2 (en) 2009-05-07 2015-04-28 Snecma Shell for aircraft turbo-engine stator with mechanical blade load transfer slits
CN102422027B (zh) * 2009-05-07 2015-05-13 斯奈克玛 用于带有机械叶片载荷转移裂隙的航空器涡轮发动机定子的壳体
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
WO2020165357A1 (fr) 2019-02-13 2020-08-20 Mitsubishi Hitachi Power Systems Europe Gmbh Injecteur de combustible à fentes de dilatation pour un brûleur à charbon pulvérisé

Also Published As

Publication number Publication date
WO2006122438A1 (fr) 2006-11-23

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