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EP1561008A1 - Aube directrice a fente - Google Patents

Aube directrice a fente

Info

Publication number
EP1561008A1
EP1561008A1 EP03753200A EP03753200A EP1561008A1 EP 1561008 A1 EP1561008 A1 EP 1561008A1 EP 03753200 A EP03753200 A EP 03753200A EP 03753200 A EP03753200 A EP 03753200A EP 1561008 A1 EP1561008 A1 EP 1561008A1
Authority
EP
European Patent Office
Prior art keywords
flow guide
nozzle ring
guide vane
slot
ring
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Withdrawn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
EP03753200A
Other languages
German (de)
English (en)
Inventor
Jozef Baets
Balz Flury
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
Publication of EP1561008A1 publication Critical patent/EP1561008A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to the field of exhaust gas turbochargers connected to internal combustion engines.
  • the invention relates to a flow guide vane for a nozzle ring according to the preamble of patent claim 1, and to a nozzle ring comprising such flow guide vanes, which is arranged in the inflow channel of a scooped exhaust gas turbine and directs the working medium onto the blades of the turbine.
  • 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 its kinetic energy is used for the intake and compression of air for the internal combustion engine.
  • a nozzle ring is arranged coaxially to the shaft of the turbine, which guides the exhaust gases onto the blades of the turbine.
  • the exhaust gas turbine sooner or later becomes contaminated with the rotor blades and the nozzle ring, the latter being significantly more affected.
  • a hard layer of dirt forms on the nozzle ring.
  • a device and a method for wet cleaning the nozzle ring of an exhaust gas turbocharger turbine is described in EP 0 781 897 B1.
  • a special design of the gas inlet housing enables water to be injected into the area immediately in front of the nozzle ring. After being injected into the exhaust gas stream of the internal combustion engine, the relatively cold water is carried by the latter to the nozzle ring. There it encounters the dirt deposits in the nozzle ring, which are suddenly cooled very strongly by the evaporation of the water on the surface. The water penetrates into the dirt layer and the deposits are partially dissolved. By applying this thermal shock treatment several times, a clean nozzle ring is achieved.
  • the invention as defined in the claims is therefore based on the object of creating nozzle ring flow guide vanes of the type mentioned which can withstand the increased thermal loads of wet cleaning of the nozzle ring with cold water when the internal combustion engine is operating with a non-reduced load.
  • the nozzle ring flow guide vane according to the preamble of claim 1, which comprises a thin trailing edge area, is characterized in that in the flow guide vanes are each made in the trailing edge area at least one slot in the flow guide vane surface.
  • FIG. 1 is a partial view of a nozzle ring with a nozzle ring flow guide vane according to the invention
  • FIG. 2 is a partial view of a nozzle ring with a slotted outer ring
  • FIG 3 shows a partial view of a nozzle ring with a nozzle ring flow guide vane according to the prior art with the thermal stress distribution during wet cleaning with cold water
  • Fig. 4 is a partial view of the nozzle ring with the inventive nozzle ring flow guide vane according to Fig. 1 with the thermal stress distribution during wet cleaning with cold water.
  • FIG. 1 shows part of an axially flowed-through nozzle ring, which comprises two fastening elements in the form of an inner ring 21 and an outer ring 22 with flow guide vanes 3 arranged therebetween.
  • the inner, outer ring and flow guide vanes are usually made from one piece.
  • the nozzle ring can also be formed in two or more parts, for example by integrally casting only the flow guide vanes and the inner ring or the flow guide vanes and the outer ring and fastening them to the corresponding further fastening element via the flow guide vanes.
  • the two fastening elements are likewise designed as rings, which, however, are arranged on both sides of the flow guide vanes in the axial direction.
  • the flow guide vanes 3 have a streamlined profile. In operation, the working medium flows along the surface 33 of the flow guide vanes 3 while being deflected by them in the desired direction. In the area of the rear edge 31, the flow guide vanes 3 are designed to be correspondingly thin in order to reduce fluidic losses. According to the invention, a slot 4 is let into this thin region 32. Instead of one slot, the flow guide vanes can also have several slots.
  • the arrangement of the one or more slots along the blade height on the blade rear edge is a question of the size and geometry of the blade.
  • the arrangement of the blade in the nozzle ring must also be taken into account.
  • the one or more slots are arranged along the blade height in the area of the greatest thermal stress of the flow guide vane, which occur when the hot flow guide vane is quenched with cleaning water that is as cold as possible to achieve the cleaning effect mentioned at the beginning. Thanks to the one or more slots, the thermal tension is largely released. This relaxation is greatest when a slot is arranged in the area of the blade which is directly illuminated with the cold water during cleaning. The thermal shock and the resulting tensions are usually the greatest in this area.
  • the slot 4 runs essentially at a right angle to the rear edge 31. In general, it runs in the flow direction of the working medium, which is deflected by the flow guide vanes. This results in lower fluidic losses.
  • the direction of flow depends on the geometry of the blade and the arrangement of the blade in the nozzle ring. With conventional blades, there are angles between the direction of flow and the rear edge in the range of around 70 to 110 degrees.
  • the slot 4 is advantageously made as thin as possible, whereas the thermal expansion of the blade requires a certain minimum width.
  • the slot can have a variable width to accommodate different, thermally induced expansion of the different thickness areas of the blade.
  • the length of the slot 4 results from the width of the highly stressed area. This depends on the size and profile of the bucket. The longer the thin area of the blade trailing edge, the longer the corresponding slot must be in order to achieve the desired effect of relieving the trailing edge area. With conventional blades, the length of the slot is around a quarter of the blade chord length.
  • the slots in the guide blades are advantageously arranged upstream at the level of these flow-disturbing elements. Since the flow disturbances caused by these elements and the slots lie one behind the other in the flow direction, the overall, unavoidable flow disturbance is not additionally increased.
  • FIG. 2 shows a section of a nozzle ring, in which the outer ring 22 has ring slots 23.
  • the slots 4 according to the invention in the flow guide blades 3 have been omitted in a simplified manner in FIG. 2, but it has been shown that the interaction of the latter with the ring slots 23 allows an optimal voltage reduction in the entire nozzle ring.
  • the ring slots 23 are distributed uniformly over the entire circumference of the outer ring 22 and are preferably to be provided centrally between two flow guide vanes 3.
  • the highly loaded area is divided by a slot.
  • the two-part area in the middle of the rear edge can expand during the rapid cooling, without the bucket threatening to dry out as a whole.
  • an extension of the slot can be arranged in the area of the end of the slot. As indicated in FIG. 1, this can be, for example, an additional bore 41 running transversely to the slot 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une couronne directrice comprenant deux éléments de fixation (21, 22) et, entre ces deux éléments de fixation, des aubes directrices (3). Les aubes directrices (3) ont un profil en forme de lignes d'écoulement. Dans la zone de leur bord arrière (31), les aubes directrices (3) sont minces de manière correspondante afin de réduire les pertes relatives à la technique des fluides. Une fente (4) est pratiquée dans cette zone (32) de conception mince. Cette fente permet, lors du nettoyage par voie humide de la couronne directrice à l'eau froide, une nette réduction des contraintes thermiques à grande surface de manière à éviter tout forte déformation des aubes directrices à des températures élevées.
EP03753200A 2002-11-13 2003-10-24 Aube directrice a fente Withdrawn EP1561008A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH19052002 2002-11-13
CH190502 2002-11-13
PCT/CH2003/000696 WO2004044387A1 (fr) 2002-11-13 2003-10-24 Aube directrice a fente

Publications (1)

Publication Number Publication Date
EP1561008A1 true EP1561008A1 (fr) 2005-08-10

Family

ID=32304043

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03753200A Withdrawn EP1561008A1 (fr) 2002-11-13 2003-10-24 Aube directrice a fente

Country Status (3)

Country Link
EP (1) EP1561008A1 (fr)
AU (1) AU2003271491A1 (fr)
WO (1) WO2004044387A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12123391B2 (en) 2023-01-10 2024-10-22 United Arab Emirates University Wind turbine blade having air passage with air cleaning member

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1724443A1 (fr) * 2005-05-20 2006-11-22 ABB Turbo Systems AG Couronne directrice
FR2945331B1 (fr) * 2009-05-07 2011-07-22 Snecma Virole pour stator de turbomoteur d'aeronef a fentes de dechargement mecanique d'aubes.

Family Cites Families (11)

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Publication number Priority date Publication date Assignee Title
BE446099A (fr) * 1943-04-16 1900-01-01
NL81546C (fr) * 1952-07-22 1955-12-15
DE2144600A1 (de) * 1971-09-07 1973-03-15 Maschf Augsburg Nuernberg Ag Verwundene und verjuengte laufschaufel fuer axiale turbomaschinen
DE2515444B2 (de) * 1975-04-09 1977-05-18 Maschinenfabrik Augsburg-Nürnberg AG, 8500 Nürnberg Laufschaufelkranz grosser umfangsgeschwindigkeit fuer thermische, axial durchstroemte turbinen
DE2849747A1 (de) * 1978-11-16 1980-05-29 Volkswagenwerk Ag Aus keramischen werkstoffen bestehender axial-leitschaufelkranz fuer gasturbinen
JPH01163404A (ja) * 1987-12-17 1989-06-27 Toshiba Corp 軸流タービンノズル
CH687347A5 (de) * 1993-04-08 1996-11-15 Abb Management Ag Wärmeerzeuger.
JP2000145404A (ja) * 1998-11-10 2000-05-26 Hitachi Ltd 蒸気タービンの湿分飛散防止構造
GB2355288B (en) * 1999-10-12 2003-10-01 Rolls Royce Plc Improved turbine blade and manufacture thereof
WO2001056703A1 (fr) * 2000-02-03 2001-08-09 Corning Incorporated Buse de bruleur refractaire pourvue de fentes de detente des contraintes
US6390775B1 (en) * 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2004044387A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12123391B2 (en) 2023-01-10 2024-10-22 United Arab Emirates University Wind turbine blade having air passage with air cleaning member

Also Published As

Publication number Publication date
AU2003271491A1 (en) 2004-06-03
WO2004044387A1 (fr) 2004-05-27

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