WO2004044387A1 - Aube directrice a fente - Google Patents
Aube directrice a fente Download PDFInfo
- 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
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
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AU2003271491A AU2003271491A1 (en) | 2002-11-13 | 2003-10-24 | Slotted guide vane |
EP03753200A EP1561008A1 (fr) | 2002-11-13 | 2003-10-24 | Aube directrice a fente |
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)
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)
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 |
-
2003
- 2003-10-24 WO PCT/CH2003/000696 patent/WO2004044387A1/fr not_active Application Discontinuation
- 2003-10-24 AU AU2003271491A patent/AU2003271491A1/en not_active Abandoned
- 2003-10-24 EP EP03753200A patent/EP1561008A1/fr not_active Withdrawn
Patent Citations (11)
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)
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)
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 |
---|---|
AU2003271491A1 (en) | 2004-06-03 |
EP1561008A1 (fr) | 2005-08-10 |
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