EP1820938A1 - Eléments de nettoyage sur les extrémités des aubes d' une turbine - Google Patents

Eléments de nettoyage sur les extrémités des aubes d' une turbine Download PDF

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Publication number
EP1820938A1
EP1820938A1 EP06405074A EP06405074A EP1820938A1 EP 1820938 A1 EP1820938 A1 EP 1820938A1 EP 06405074 A EP06405074 A EP 06405074A EP 06405074 A EP06405074 A EP 06405074A EP 1820938 A1 EP1820938 A1 EP 1820938A1
Authority
EP
European Patent Office
Prior art keywords
exhaust gas
blades
gas turbine
cleaning
turbine
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Withdrawn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
EP06405074A
Other languages
German (de)
English (en)
Inventor
Christoph Mathey
Markus Loos
William Gizzi
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 EP06405074A priority Critical patent/EP1820938A1/fr
Publication of EP1820938A1 publication Critical patent/EP1820938A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Definitions

  • the invention relates to the field of turbomachines subjected to exhaust gases of internal combustion engines.
  • It relates to a cleaning device of an exhaust gas turbine.
  • Exhaust gas turbines in particular in exhaust gas turbochargers, are used in conjunction with an internal combustion engine.
  • the exhaust gas from the internal combustion engine is used as a drive means for driving the turbine wheel.
  • the turbine wheel is connected by a shaft to the compressor wheel with which the intake air, which is supplied to the internal combustion engine, is compressed.
  • the exhaust gas carried on the blades of the exhaust gas turbine contains impurities caused by incomplete combustion and fuel contamination. The amount of impurities that the internal combustion engine emits with the exhaust gas is heavily dependent on the fuel used. If a dirty fuel is used, such as heavy fuel oil (HFO), significant amounts of pollutants can be released with the exhaust gas.
  • HFO heavy fuel oil
  • the impurities in the exhaust gas lead to deposits on the housing parts forming the flow channel around the turbine wheel. Particularly in the area radially outside the rapidly rotating blades, deposits are increasingly generated by the dirt particles displaced radially outward. These deposits tend to reduce the air gap (clearance) formed between the tips of the blades and the opposing body portions, and sooner or later contact between the deposits and the blades occurs. As a result, on the one hand, the turbine wheel is braked, On the other hand, however, the blades can be damaged by the blade tips are abraded by the constant friction.
  • the contaminated parts are usually freed from the deposits at regular intervals by means of a cleaning liquid injected into the exhaust gas flow in the flow channel.
  • An axial turbine is known with a device for introducing a cleaning medium into the blade channel.
  • a cleaning medium leading and provided with exit points, a ring-forming nozzle carrier is disclosed, which is arranged radially outside the inflow channel at the inlet into the blade channel of the turbine.
  • a similar device is off DE 2 008 503 known. Again, a cleaning liquid is injected at a great distance from radially outside the flow channel into the flow.
  • a device for cleaning the turbine blades of an exhaust gas turbocharger in which water is injected by means of water injection nozzles upstream of the guide elements in the exhaust gas stream.
  • the water is passed from a high pressure water supply via a water line to the individual water injectors, which then provides the appropriate stream of droplets for cleaning.
  • the object of the invention is to provide an exhaust gas turbine with a simplified cleaning device.
  • the cleaning device comprises cleaning elements arranged on the rotor blades of the exhaust-gas turbine, which continually clear the region radially outside the rotor blades of excessive contamination during operation.
  • the inventive cleaning elements are formed in a first embodiment as coated blade tips. These coated blade tips rub off the deposited on the radial inside of the housing of the exhaust turbine pollution.
  • these moving blades are advantageously designed to be longer in the radial direction than the remaining moving blades.
  • the cleaning effect is not impaired, but the manufacturing cost of the turbine wheel can be kept low.
  • the cleaning elements can be provided with cutting edges, which can be oriented radially outwards or inclined towards the pressure side.
  • the impurities are continuously planed down with the cutting edge guided almost parallel to the surface of the housing wall.
  • the impeller of an exhaust gas turbine includes a hub with blades mounted thereon. Depending on the size and scope of the exhaust gas turbine, an impeller includes between a few and several dozen blades.
  • Fig. 1 shows schematically a section through the axis of an exhaust gas turbine, wherein only a small section in the region of the rotor blades 1 and the rotor blades surrounding the housing wall 2 is shown. The direction of rotation of the turbine wheel is indicated by the arrow.
  • the rotor blade according to the invention equipped with a cleaning element 11 is formed in the illustrated embodiment in the radial direction longer than the other blades. This ensures that impurities 3, which deposit on the inside of the housing wall 2 in the course of operation of the exhaust gas turbine, are only detected by the cleaning elements, and do not affect the tips of the other blades.
  • the cleaning elements on the blade tips may comprise an abrasive coating.
  • a layer of, for example, cubic boron nitrides (cBN), chromium carbide (CrC) or tungsten carbide-chromium carbide non-rods (WC-CrC-Ni) or similar, abrasion-resistant materials is applied to the blade tip of the relevant rotor blades.
  • the coating may comprise the entire blade tip of the blade, or only on the pressure side, i. be mounted on the front side in the direction of the turbine wheel, and not on the suction side.
  • the coated blade tip as a cleaning element has the advantage that even with prolonged operation and heavy contamination, the blade is not damaged at the radially outer tip.
  • the tip is also not shortened in the radial direction, so that the air gap between the housing wall and the other, equipped without cleaning element blades can be kept constant. The maintenance of the cleaning element allows permanent cleaning of the area radially outside the blades.
  • FIG. 2 shows a second embodiment of the cleaning element according to the invention.
  • a cutting edge 12 is provided in the radially outermost region of the blade tip.
  • This cutting edge which is advantageously also made of an abrasion-resistant material 11 or coated with such, ensures a clean cut through the deposits on the inside of the housing wall. If the cutting edge, as shown in Fig. 3, in the direction of the pressure side, ie in the running direction of the turbine wheel, inclined, the Cutting effect can be additionally improved.
  • the uppermost layer of the deposit is continuously planed with the cutting edge guided almost parallel to the surface of the deposit. The resistance of the cleaning element when removing the deposit can be reduced thanks to the cutting edge.
  • the removed pollution is detected by the flow and fed with the exhaust gas to the exhaust pipes. If necessary, these particles are filtered with suitable filters from the exhaust gases.
  • the cleaning device according to the invention is advantageously combined with a wet cleaning device known from the prior art.
  • the sudden injection of cold cleaning fluid the distance between the blade tips and the surrounding housing parts may be subject to short-term thermal changes.
  • the longer cleaning elements on the blade tips ensure that the remaining blades are not impaired.
  • the cleaning elements according to the invention can be used both in the case of axial-flow exhaust gas turbines, the so-called axial turbines, and also in the case of exhaust gas turbines flowed radially or mixed, the so-called radial or mixed flow turbines.
  • Such exhaust gas turbines can be used in exhaust gas turbochargers for driving a compressor or in power turbines for driving an electric generator.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP06405074A 2006-02-20 2006-02-20 Eléments de nettoyage sur les extrémités des aubes d' une turbine Withdrawn EP1820938A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06405074A EP1820938A1 (fr) 2006-02-20 2006-02-20 Eléments de nettoyage sur les extrémités des aubes d' une turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06405074A EP1820938A1 (fr) 2006-02-20 2006-02-20 Eléments de nettoyage sur les extrémités des aubes d' une turbine

Publications (1)

Publication Number Publication Date
EP1820938A1 true EP1820938A1 (fr) 2007-08-22

Family

ID=36685747

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06405074A Withdrawn EP1820938A1 (fr) 2006-02-20 2006-02-20 Eléments de nettoyage sur les extrémités des aubes d' une turbine

Country Status (1)

Country Link
EP (1) EP1820938A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2204548A1 (fr) 2009-01-06 2010-07-07 ABB Turbo Systems AG Turbine de gaz d'échappement avec virole et turbochargeur d'échappement associé
WO2011002570A1 (fr) * 2009-06-30 2011-01-06 General Electric Company Pale de rotor et procédé de réduction de la charge de friction des extrémités
FR2962762A1 (fr) * 2010-07-19 2012-01-20 Snecma Aube de compresseur dans une turbomachine
US8657570B2 (en) 2009-06-30 2014-02-25 General Electric Company Rotor blade with reduced rub loading
US8662834B2 (en) 2009-06-30 2014-03-04 General Electric Company Method for reducing tip rub loading
CN108869032A (zh) * 2018-02-23 2018-11-23 孙远 一种汽车涡轮增压系统的清洗方法
EP3546703A1 (fr) * 2018-03-29 2019-10-02 Siemens Aktiengesellschaft Aube mobile de turbine pour une turbine à gaz

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH335901A (de) 1955-11-10 1959-01-31 Sulzer Ag Turbine mit einer Einrichtung zum Einführen eines Reinigungsmediums in den Schaufelkanal
DE2008503A1 (de) 1969-07-28 1971-02-11 VEB Bergmann Borsig/Gorlitzer Ma schinenbau, Werk Berlin, Berlin Einrichtung zum Waschen der Schaufeln von Gasturbinen
DE3102575A1 (de) * 1980-05-01 1982-01-28 General Electric Co., Schenectady, N.Y. "spitzenkappe fuer eine rotorschaufel und verfahren zum austauschen derselben"
DE3515825A1 (de) 1984-05-11 1985-11-14 Elliott Turbomachinery Co., Inc., Jeannette, Pa. Verfahren und vorrichtung zum steuern des reinigens der turbinenlaufschaufeln eines abgasturboladers
GB2225388A (en) * 1988-10-01 1990-05-30 Rolls Royce Plc Rotor blade tip clearance setting in gas turbine engines
EP0702130A2 (fr) * 1994-09-16 1996-03-20 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Extrémité d'aube avec un revêtement coupant
WO2002025065A1 (fr) * 2000-09-25 2002-03-28 Alstom (Switzerland) Ltd Systeme de garniture d'etancheite

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH335901A (de) 1955-11-10 1959-01-31 Sulzer Ag Turbine mit einer Einrichtung zum Einführen eines Reinigungsmediums in den Schaufelkanal
DE2008503A1 (de) 1969-07-28 1971-02-11 VEB Bergmann Borsig/Gorlitzer Ma schinenbau, Werk Berlin, Berlin Einrichtung zum Waschen der Schaufeln von Gasturbinen
DE3102575A1 (de) * 1980-05-01 1982-01-28 General Electric Co., Schenectady, N.Y. "spitzenkappe fuer eine rotorschaufel und verfahren zum austauschen derselben"
DE3515825A1 (de) 1984-05-11 1985-11-14 Elliott Turbomachinery Co., Inc., Jeannette, Pa. Verfahren und vorrichtung zum steuern des reinigens der turbinenlaufschaufeln eines abgasturboladers
GB2225388A (en) * 1988-10-01 1990-05-30 Rolls Royce Plc Rotor blade tip clearance setting in gas turbine engines
EP0702130A2 (fr) * 1994-09-16 1996-03-20 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Extrémité d'aube avec un revêtement coupant
WO2002025065A1 (fr) * 2000-09-25 2002-03-28 Alstom (Switzerland) Ltd Systeme de garniture d'etancheite

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2204548A1 (fr) 2009-01-06 2010-07-07 ABB Turbo Systems AG Turbine de gaz d'échappement avec virole et turbochargeur d'échappement associé
WO2011002570A1 (fr) * 2009-06-30 2011-01-06 General Electric Company Pale de rotor et procédé de réduction de la charge de friction des extrémités
US8657570B2 (en) 2009-06-30 2014-02-25 General Electric Company Rotor blade with reduced rub loading
US8662834B2 (en) 2009-06-30 2014-03-04 General Electric Company Method for reducing tip rub loading
FR2962762A1 (fr) * 2010-07-19 2012-01-20 Snecma Aube de compresseur dans une turbomachine
CN108869032A (zh) * 2018-02-23 2018-11-23 孙远 一种汽车涡轮增压系统的清洗方法
EP3546703A1 (fr) * 2018-03-29 2019-10-02 Siemens Aktiengesellschaft Aube mobile de turbine pour une turbine à gaz
WO2019185713A1 (fr) 2018-03-29 2019-10-03 Siemens Aktiengesellschaft Pale de turbine pour turbine à gaz

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