WO2004044387A1 - Aube directrice a fente - Google Patents

Aube directrice a fente Download PDF

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Publication number
WO2004044387A1
WO2004044387A1 PCT/CH2003/000696 CH0300696W WO2004044387A1 WO 2004044387 A1 WO2004044387 A1 WO 2004044387A1 CH 0300696 W CH0300696 W CH 0300696W WO 2004044387 A1 WO2004044387 A1 WO 2004044387A1
Authority
WO
WIPO (PCT)
Prior art keywords
flow guide
nozzle ring
guide vane
slot
ring
Prior art date
Application number
PCT/CH2003/000696
Other languages
German (de)
English (en)
Inventor
Jozef Baets
Balz Flury
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 EP03753200A priority Critical patent/EP1561008A1/fr
Priority to AU2003271491A priority patent/AU2003271491A1/en
Publication of WO2004044387A1 publication Critical patent/WO2004044387A1/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
    • 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.
  • 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.
  • 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.

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.
PCT/CH2003/000696 2002-11-13 2003-10-24 Aube directrice a fente WO2004044387A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP03753200A EP1561008A1 (fr) 2002-11-13 2003-10-24 Aube directrice a fente
AU2003271491A AU2003271491A1 (en) 2002-11-13 2003-10-24 Slotted guide vane

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1905/02 2002-11-13
CH19052002 2002-11-13

Publications (1)

Publication Number Publication Date
WO2004044387A1 true WO2004044387A1 (fr) 2004-05-27

Family

ID=32304043

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CH2003/000696 WO2004044387A1 (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 (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
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

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB616099A (en) * 1943-04-16 1949-01-17 British Thomson Houston Co Ltd Improvements in and relating to blades of the kind used for the rotor and stator elements of compressors, turbines and like elastic fluid apparatus
GB732622A (en) * 1952-07-22 1955-06-29 Bbc Brown Boveri & Cie Oscillation dampers for the blades of steam and gas turbines, axial flow compressors and similar machines
DE2144600A1 (de) * 1971-09-07 1973-03-15 Maschf Augsburg Nuernberg Ag Verwundene und verjuengte laufschaufel fuer axiale turbomaschinen
US4102600A (en) * 1975-04-09 1978-07-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Moving blade ring of high circumferential speed for thermal axially passed through turbines
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
DE4406399A1 (de) * 1993-04-08 1994-10-13 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
WO2001056703A1 (fr) * 2000-02-03 2001-08-09 Corning Incorporated Buse de bruleur refractaire pourvue de fentes de detente des contraintes
US6358013B1 (en) * 1999-10-12 2002-03-19 Rolls-Royce Plc Turbine blade and manufacture thereof
US6390775B1 (en) * 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB616099A (en) * 1943-04-16 1949-01-17 British Thomson Houston Co Ltd Improvements in and relating to blades of the kind used for the rotor and stator elements of compressors, turbines and like elastic fluid apparatus
GB732622A (en) * 1952-07-22 1955-06-29 Bbc Brown Boveri & Cie Oscillation dampers for the blades of steam and gas turbines, axial flow compressors and similar machines
DE2144600A1 (de) * 1971-09-07 1973-03-15 Maschf Augsburg Nuernberg Ag Verwundene und verjuengte laufschaufel fuer axiale turbomaschinen
US4102600A (en) * 1975-04-09 1978-07-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Moving blade ring of high circumferential speed for thermal axially passed through turbines
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
DE4406399A1 (de) * 1993-04-08 1994-10-13 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
US6358013B1 (en) * 1999-10-12 2002-03-19 Rolls-Royce Plc 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 (2)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 013, no. 425 (M - 873) 21 September 1989 (1989-09-21) *
PATENT ABSTRACTS OF JAPAN vol. 2000, no. 08 6 October 2000 (2000-10-06) *

Cited By (3)

* 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
WO2006122438A1 (fr) * 2005-05-20 2006-11-23 Abb Turbo Systems Ag Couronne directrice
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

Also Published As

Publication number Publication date
EP1561008A1 (fr) 2005-08-10
AU2003271491A1 (en) 2004-06-03

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