EP2112332B1 - Anneau support de distributeur avec canal pressurisé - Google Patents

Anneau support de distributeur avec canal pressurisé Download PDF

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Publication number
EP2112332B1
EP2112332B1 EP20080154983 EP08154983A EP2112332B1 EP 2112332 B1 EP2112332 B1 EP 2112332B1 EP 20080154983 EP20080154983 EP 20080154983 EP 08154983 A EP08154983 A EP 08154983A EP 2112332 B1 EP2112332 B1 EP 2112332B1
Authority
EP
European Patent Office
Prior art keywords
air
supporting ring
sealed channel
turbomachine
vane assembly
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.)
Active
Application number
EP20080154983
Other languages
German (de)
English (en)
Other versions
EP2112332A1 (fr
Inventor
Peter Neuenschwander
Matthias Jarusel
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 EP20080154983 priority Critical patent/EP2112332B1/fr
Priority to JP2011505504A priority patent/JP5021846B2/ja
Priority to KR1020107022843A priority patent/KR101244956B1/ko
Priority to CN200980115076.6A priority patent/CN102016237B/zh
Priority to PCT/EP2009/054857 priority patent/WO2009130262A1/fr
Publication of EP2112332A1 publication Critical patent/EP2112332A1/fr
Application granted granted Critical
Publication of EP2112332B1 publication Critical patent/EP2112332B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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

Definitions

  • the invention relates to the field of guide devices for turbomachines, in particular for turbines of turbochargers for supercharged internal combustion engines.
  • It relates to a support ring of a guide device with adjustable guide vanes, guide devices with such a support ring, as well as flow machines with such guide devices with such a support ring.
  • Exhaust gas turbochargers are used to increase the performance of internal combustion engines (reciprocating engines).
  • An exhaust gas turbocharger consists of an exhaust gas turbine in the exhaust gas stream of the internal combustion engine and a compressor in the intake tract of the internal combustion engine.
  • the turbine wheel of the exhaust gas turbine is set in rotation by the exhaust gas flow of the internal combustion engine and drives the impeller of the compressor via a shaft.
  • the compressor increases the pressure in the intake tract of the internal combustion engine, so that when sucking a larger amount of air enters the combustion chambers.
  • Exhaust gas turbines are also used as power turbines. In this case, they do not drive the compressor of an exhaust gas turbocharger via the shaft, but rather a generator or via a clutch another mechanical useful part.
  • turbochargers with turbine and compressor components with fixed geometries have been used predominantly for large engines (fixed geometries). These geometries have been designed and adapted for each individual engine. During the operation of the engine, however, they were invariable. In the future an even better adaptation of the exhaust gas turbocharger To enable the engine during operation, the use of adjustable in operation (or variable) turbine geometries (VTG) is increasingly up for discussion. In this case, the opening of the guide vanes of the guide device of the exhaust gas turbine is varied by a rotation of the guide vanes.
  • variable turbine geometries are well known in the art and particularly in the field of small engines, such as those used in passenger cars.
  • variable turbine geometries are already being used today for gas engines which require precise regulation of the fuel / air ratio.
  • widespread use of variable turbine geometries in large engines is to be expected.
  • the guide In order to prevent the exhaust gases of the internal combustion engine in the bearing points of the guide vanes of the guide in exhaust gas turbochargers with variable turbine geometry and to exclude the leakage of exhaust gases into the environment, the guide must be supplied with air purge.
  • the sealing air is guided in an inside of the cross-sectional profile of the bearing housing ring - hereinafter referred to as a support ring - the guide device arranged annular channel.
  • a support ring - the guide device arranged annular channel.
  • the cross section of the sealing air duct is relatively small due to the limited space inside the profile of the support ring. In order to achieve a uniform supply of sealing air, the air must therefore be supplied in several places. For this purpose, other special pipes are needed outside the guide.
  • US20080075583 discloses a guide device of a turbine which has rotatably mounted guide vanes in the turbine housing. Between the turbine housing and the rotatably mounted in the turbine housing Leitschaufelschaft a sealing sleeve is arranged. An additional axial compression spring ensures that the sealing sleeve is pressed continuously against a guide blade counter contour and thereby an axial gap and the leakage flow through the bearing point of the Leitschaufel textilefte be prevented. Further, a barrier air supply is disclosed, which introduces sealing air in the region between the guide vane bearing point and the flow channel of the turbine.
  • the object of the invention is to provide a cost-effective to manufacture support ring of a guide device of a turbomachine.
  • this is achieved with a support ring, wherein the barrier air channel for preventing the ingress of gases from the flow channel into the bearing points of the guide vanes of the guide device as an outward opening and extending in the circumferential direction groove or channel is formed.
  • the groove is embedded in an axial end face of the carrier ring.
  • the groove is embedded in a radially outer side or inner side of the shell. If the barrier air duct designed as an open channel in the support ring, the support ring can thereby be poured without a core for the sealing air duct.
  • the embedded in an axial end face or a shell side of the carrier ring sealing air channel is sealed according to the invention on its open side by the gas outlet housing and / or another housing part, such as the cover.
  • the barrier air channel of the carrier ring formed according to the invention can have such a large cross-section that the entire barrier air can be supplied only at one point along the circumference. This makes it possible to save the distribution pipes and requires a smaller number of mechanical processing of the support ring. Further advantages emerge from the dependent claims.
  • Fig. 1 shows a conventional exhaust gas turbocharger with exhaust gas turbine 20 and compressor 10, and disposed therebetween bearing housing 50.
  • the exhaust gas turbine 20 includes a gas inlet housing 21 through which the hot exhaust gas flows to the turbine and this drives before the exhaust gas is supplied through the gas outlet housing 22 of the exhaust system.
  • the turbine wheel is arranged at one end of a shaft rotatable about the axis A, which is rotatably mounted in the bearing housing 50.
  • the compressor wheel At the other end of the shaft is the compressor wheel, which compresses air drawn in through the air inlet housing 11, which air is subsequently collected in the air outlet housing 21 and fed to the combustion chambers of the internal combustion engine.
  • the turbine is an axial flowed axial turbine.
  • Fig. 2 shows a section of an axial turbine of a conventional exhaust gas turbocharger.
  • the turbine wheel 25 is arranged on the shaft 30 which is rotatable about the axis A in the bearing housing 50.
  • the turbine wheel 25 includes a plurality of blades 26, which are distributed along the circumference of the radially outer edge of the turbine wheel.
  • the exhaust gas flow in the flow channel from the gas inlet housing 21 to the gas outlet housing 22 is indicated in the figures in each case by arrows. The blades of the turbine wheel are flowed in the axial direction.
  • an adjustable guide (adjustable turbine geometry) is arranged upstream of the rotor blades 26 of the exhaust turbine.
  • This adjustable guide device comprises a plurality of guide vanes 41, which each have a shaft 42.
  • Each of the guide vanes 41 is mounted in each case with its shaft 42 about the axis B rotatably in the housing.
  • the housing of the guide device comprises a support ring 40, which encloses the flow channel in an annular manner. Towards the flow channel, the support ring 40 can still enclose a cover ring 45.
  • the shafts 42 of the guide vanes 41 are arranged in the support ring 40 in holes provided and stored. These bearings run, as the shafts 42 of the vanes 41, substantially in the radial direction.
  • the support ring 40 is usually fastened with fastening means on the gas outlet housing 22 and / or on the gas inlet housing 21. As fasteners bolts, screws or tabs are used.
  • the adjustable guide device further comprises an adjusting ring 43 and per guide vane an adjusting lever 44, which are guided through openings 49 in the support ring to the shaft 42. To adjust the guide the adjusting ring 43 is moved in the circumferential direction. The adjustment levers 44 transmit the rotational movement to the shafts 42 of the vanes.
  • a barrier air channel 46 is arranged in the support ring 40. The sealing air is fed at one or more points in the annular inside the profile carrier ring 40 extending sealing air channel 46 and flows through the openings for the shafts of the vanes in the flow channel.
  • the openings 48 for receiving and supporting the shafts 42 of the guide vanes 41 are in turn supplied with sealing air via a sealing air channel 46.
  • the sealing air channel 46 is sealed with sealing elements 47, so that no blocking air can escape in this direction along the shank of the guide vanes.
  • the barrier air channel 46 is designed as a groove let into the axial end face of the carrier ring 40, as well as the schematic representations of the axially flow-through guide device 4 and FIG. 5 can be removed.
  • the sealing air channel 46 When installed, the sealing air channel 46 is bounded by the adjacent to the axial end face housing part 22. This results in the recessed as a groove in the support ring 40 sealing air channel 46 in the installed state, an annular cavity. To increase the cross section of the sealing air channel, a groove 23 opening in the axial direction can be introduced on the side of the housing.
  • the sealing air channel is composed of the carrier ring-side sealing air channel 46 and the housing-side groove 23.
  • the contact surfaces between the carrier ring and the adjacent housing parts may be flat, inclined or stepped in the region of the sealing air channel.
  • the groove 23 widening the sealing air channel can extend on the side of the housing into the region of the cover ring 45.
  • the cross section can be further enlarged.
  • the sealing air channel can be sealed by sealing elements 47 arranged radially inside and / or outside the sealing air channel. This makes it possible to prevent the sealing air fed into the barrier air channel 46 with excess pressure from escaping through the connection between the gas outlet housing 22 and the carrier ring 40.
  • the groove which forms the sealing air channel 46 can also be embedded on the end face of the carrier ring 40 facing the gas inlet housing 21.
  • the grooves forming the sealing air channel in the carrier ring and / or in the adjacent housing may be formed as annular groove segments, that is to say they may be divided along the circumference into a plurality of sections.
  • Each barrier air duct segment can be supplied individually with external air from the outside.
  • Fig. 6 relates to an example of a guide, which is not part of the invention.
  • the figure shows a section through the support ring of a radially flowed guide device, as used for example in radial or mixed flow turbine.
  • the sealing air channel 46 is formed by a radially outwardly or radially inwardly opening groove in the support ring.
  • This groove forming the barrier air channel 46 is thus embedded in a lateral surface of the carrier ring 40.
  • the limitation of the groove to the annular cavity is effected by an adjacent housing part, in the case of an exhaust gas turbine this would be about the gas inlet housing 21.
  • a circumferential groove 23 can be inserted to expand the sealing air channel 46 in the adjacent housing part.

Claims (9)

  1. Anneau de support (40) d'un dispositif directeur d'une turbine axiale comprenant des aubes directrices réglables (41), l'anneau de support entourant de manière annulaire un canal d'écoulement et l'anneau de support comprenant des ouvertures (48) pour recevoir et supporter à rotation des axes (42) des aubes directrices disposées dans le canal d'écoulement et un canal d'air d'étanchéité (46) pour l'alimentation en air d'étanchéité dans le dispositif directeur, et le canal d'air d'étanchéité (46) débouchant dans les ouvertures (48) pour recevoir et supporter à rotation les axes des aubes (42), caractérisé en ce que le canal d'air d'étanchéité (46) est pratiqué sous forme de rainure s'étendant dans la direction périphérique, ouvrant vers l'extérieur, dans un côté extérieur de l'anneau de support (40), de sorte que l'air d'étanchéité s'écoule dans le canal d'écoulement hors de la rainure pratiquée dans l'anneau de support à travers les ouvertures (48) dans l'anneau de support (40) pour recevoir et supporter à rotation les axes des aubes (42).
  2. Anneau de support selon la revendication 1, dans lequel le canal d'air d'étanchéité (46) est divisé le long de la périphérie en plusieurs segments de rainure annulaire.
  3. Dispositif directeur comprenant un anneau de support selon l'une quelconque des revendications 1 ou 2, dans lequel le dispositif directeur présente des aubes directrices réglables, les aubes directrices (41) présentant à chaque fois un axe (42) qui est supporté à rotation à chaque fois dans une ouverture (48) de l'anneau de support (40).
  4. Dispositif directeur comprenant des aubes directrices réglables (41) selon la revendication 3, dans lequel le canal d'air d'étanchéité (46) est pratiqué sous forme de rainure ouverte dans la direction axiale, s'étendant dans la direction périphérique, dans un côté frontal axial de l'anneau de support (40).
  5. Turbomachine, comprenant un boîtier (22) ainsi qu'un dispositif directeur selon la revendication 4, dans laquelle l'anneau de support (40) repose avec le côté frontal présentant le canal d'air d'étanchéité (46) sur le boîtier (22) de la turbomachine, de telle sorte que le boîtier (22) limite le canal d'air d'étanchéité (46) dans la direction axiale.
  6. Turbomachine selon la revendication 6, dans laquelle, dans le boîtier (22) dans la région de la limitation axiale du canal d'air d'étanchéité (46), est pratiquée une rainure (23) s'étendant dans la direction périphérique, ouverte dans la direction axiale et vers le canal d'air d'étanchéité (46) dans l'anneau de support (40).
  7. Turbomachine selon l'une quelconque des revendications 5 ou 6, dans laquelle, pour étancher le canal d'air d'étanchéité (46) dans la région de transition entre l'anneau de support (40) et le boîtier de la turbomachine, on dispose des éléments d'étanchéité (47).
  8. Turbomachine selon l'une quelconque des revendications 5 à 7, dans laquelle la turbomachine est une turbine à gaz d'échappement.
  9. Turbocompresseur à gaz d'échappement, comprenant une turbomachine selon la revendication 8.
EP20080154983 2008-04-23 2008-04-23 Anneau support de distributeur avec canal pressurisé Active EP2112332B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP20080154983 EP2112332B1 (fr) 2008-04-23 2008-04-23 Anneau support de distributeur avec canal pressurisé
JP2011505504A JP5021846B2 (ja) 2008-04-23 2009-04-23 遮断空気通路を有するガイド装置の支持リング
KR1020107022843A KR101244956B1 (ko) 2008-04-23 2009-04-23 실링 에어 채널을 가진 안내 장치의 캐리어 링
CN200980115076.6A CN102016237B (zh) 2008-04-23 2009-04-23 带有密封空气通道的引导装置的支撑环
PCT/EP2009/054857 WO2009130262A1 (fr) 2008-04-23 2009-04-23 Bague de support pour un dispositif de guidage avec canal d’air de retenue

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20080154983 EP2112332B1 (fr) 2008-04-23 2008-04-23 Anneau support de distributeur avec canal pressurisé

Publications (2)

Publication Number Publication Date
EP2112332A1 EP2112332A1 (fr) 2009-10-28
EP2112332B1 true EP2112332B1 (fr) 2012-08-15

Family

ID=40551991

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20080154983 Active EP2112332B1 (fr) 2008-04-23 2008-04-23 Anneau support de distributeur avec canal pressurisé

Country Status (5)

Country Link
EP (1) EP2112332B1 (fr)
JP (1) JP5021846B2 (fr)
KR (1) KR101244956B1 (fr)
CN (1) CN102016237B (fr)
WO (1) WO2009130262A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT511072B1 (de) * 2011-06-22 2012-09-15 Avl List Gmbh Brennkraftmaschine mit zumindest einem zylinder
US9228447B2 (en) * 2012-02-14 2016-01-05 United Technologies Corporation Adjustable blade outer air seal apparatus
DE102012211950A1 (de) * 2012-07-09 2014-05-08 Abb Turbo Systems Ag Abgasturbine
FR3051840B1 (fr) * 2016-05-31 2020-01-10 Safran Aircraft Engines Carter intermediaire de turbomachine, equipee d'une piece d'etancheite a interface bras/virole
DE102016110269A1 (de) * 2016-06-03 2017-12-07 Man Diesel & Turbo Se Axialturbine eines Turboladers und Turbolader
DE102016114253A1 (de) * 2016-08-02 2018-02-08 Man Diesel & Turbo Se Axialturbine eines Turboladers und Turbolader

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214852A (en) * 1978-04-20 1980-07-29 General Electric Company Variable turbine vane assembly
DE69825959T2 (de) * 1997-06-19 2005-09-08 Mitsubishi Heavy Industries, Ltd. Vorrichtung zum dichten der leitschaufeln von gasturbinen
DE10225679A1 (de) * 2002-06-10 2003-12-18 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
DE10253693B4 (de) * 2002-11-18 2005-12-01 Borgwarner Turbo Systems Gmbh Abgasturbolader
EP1669548A1 (fr) * 2004-12-08 2006-06-14 ABB Turbo Systems AG Système d'aubes de guidage réglable pour une turbine à gaz
EP1788199A3 (fr) * 2005-11-22 2011-02-23 General Electric Company Assemblage d'aubes statoriques variables avec une couche résistant à l'usure
EP1811134A1 (fr) * 2006-01-23 2007-07-25 ABB Turbo Systems AG Dispositif de guidage réglable
EP1895106A1 (fr) 2006-08-28 2008-03-05 ABB Turbo Systems AG Joint pour des aubes variables de guidage

Also Published As

Publication number Publication date
JP2012500922A (ja) 2012-01-12
KR20100133430A (ko) 2010-12-21
WO2009130262A1 (fr) 2009-10-29
JP5021846B2 (ja) 2012-09-12
KR101244956B1 (ko) 2013-03-18
CN102016237B (zh) 2014-06-04
CN102016237A (zh) 2011-04-13
EP2112332A1 (fr) 2009-10-28

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