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EP2080871A1 - Dispositif d'actionnement des aubes de guidage variables - Google Patents

Dispositif d'actionnement des aubes de guidage variables Download PDF

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Publication number
EP2080871A1
EP2080871A1 EP08150265A EP08150265A EP2080871A1 EP 2080871 A1 EP2080871 A1 EP 2080871A1 EP 08150265 A EP08150265 A EP 08150265A EP 08150265 A EP08150265 A EP 08150265A EP 2080871 A1 EP2080871 A1 EP 2080871A1
Authority
EP
European Patent Office
Prior art keywords
guide
radius
vanes
guide device
exhaust gas
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Withdrawn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
EP08150265A
Other languages
German (de)
English (en)
Inventor
Matthias Jarusel
Peter Neuenschwander
Thorsten Bosse
Bent Phillipsen
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 EP08150265A priority Critical patent/EP2080871A1/fr
Priority to EP09701799A priority patent/EP2229508A1/fr
Priority to JP2010542606A priority patent/JP5123400B2/ja
Priority to KR1020107016534A priority patent/KR101265927B1/ko
Priority to PCT/EP2009/050258 priority patent/WO2009090149A1/fr
Priority to CN2009801027723A priority patent/CN101910566A/zh
Publication of EP2080871A1 publication Critical patent/EP2080871A1/fr
Priority to US12/835,401 priority patent/US8251647B2/en
Withdrawn legal-status Critical Current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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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 turbomachines, in particular the turbocharger for supercharged internal combustion engines. It relates to a fastening device for a guide device, with which the guide device is attached to the housing of such a turbomachine.
  • 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 but they were unchanging. 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 flow components of the turbocharger have been developed for reasons of economy for high specific flow rates (high mass flow compared to the geometric size).
  • the blades of the turbines of such turbomachinery can be exposed to high vibration excitations.
  • a very precise coordination of the guide device (nozzle ring) and the blade geometry should be made.
  • the guide blade vanes of the rotor blade are a periodic disturbance with frequency equal to number of vanes by number of revolutions. If this frequency coincides with natural frequencies of the blades, resonances can occur. The alternating voltages in these resonances can possibly lead to material damage. It is known that the resonant amplitudes increase with decreasing opening of the vanes. This can lead to the limitation of the permissible openings of the guide vanes. With the variable turbine geometry, it is important to have a large adjustment range of the vane opening. If the range of permissible vane openings has to be restricted by impermissible resonances, the benefits of the variable turbine geometry are reduced.
  • variable guide device is built in exhaust gas turbochargers for large engines usually as a separate module and attached to the gas inlet and gas outlet housings of the exhaust gas turbine, as shown in the Fig.1 is indicated.
  • the gas inlet housing and the gas outlet housing are usually freely rotatable for attachment to different motors in stages of certain angles, for example 15 °. This typically results in the use of circumferentially evenly spaced screws (for 15 ° sections this gives 24 screws). When using unevenly arranged vanes, collisions between the vanes and the screws become inevitable.
  • the object of the invention is to optimize an adjustable guide device for a turbomachine, such as an exhaust gas turbine, such that the fastening means used for attachment to the adjacent housing can be mounted independently of the orientation of the guide device to the housing.
  • the idea of the invention consists in the displacement of the attachment for the cultivation of the guide device in the region radially outside the guide vanes, in particular radially outside the guide vane shafts.
  • the circumferential position of the vanes can be freely selected within the predetermined angle.
  • the vanes can be distributed both evenly and unevenly around the circumference. For the non-uniform arrangement, the vanes are realized by uneven distribution of the guide vane receptacle in the relief ring, carrier ring and Nutenring.
  • Fig. 1 shows a section of a conventional axial turbine of an exhaust gas turbocharger.
  • the turbine wheel 10 is arranged on the shaft 30 rotatably mounted in a bearing housing about the axis A.
  • Turbine wheel 10 includes a plurality of blades 11 which are distributed along the circumference at the radially outer edge of the turbine wheel.
  • the exhaust gas flow in the flow channel is indicated by arrows.
  • the blades of the turbine wheel are flowed in the axial direction.
  • an adjustable guide device upstream of the rotor blades 11 of the exhaust gas turbine, an adjustable guide device (adjustable turbine geometry) is arranged.
  • 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 essentially 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 relief ring 45.
  • the shafts 42 of the vanes 41 are arranged in the support ring 40 in holes provided for this purpose. The holes extend, as the shafts 42 of the vanes 41, substantially in the radial direction.
  • the support ring is fastened with fastening means 50 on the gas outlet housing 20. As fasteners bolts or screws are used.
  • the adjustable guide device further comprises an adjusting ring 43 and per guide vane an adjusting lever 44. For adjusting the guide device, 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.
  • the fastening means are arranged radially outside the bearing points 46 of the guide blade shafts 42, or radially outside the free ends of the guide blade shafts.
  • the radius r 2 outside which the fastening means 50 are located is thus greater than the radius r 1 within which the guide blade shafts are located.
  • the guide vanes 41 can be both uniformly and non-uniformly distributed along the circumference of the carrier ring, without thereby the fastening means 50 and the shafts 42 of the vanes intersect each other.
  • the non-uniform arrangement of the guide vanes 41 is realized by non-uniform distribution of the guide vane receptacle in the relief ring 45, carrier ring 40 and adjusting ring.
  • the support ring 40 can be positioned at any angle with respect to the gas outlet housing 20, even with irregularly distributed vanes, which allow distributed along the circumference arranged holes for the fasteners.
  • the circumferential position of the guide vanes can thus be freely selected within the predetermined angle.
  • the gas inlet housing 21 can be radially connected within the adjusting lever 44 with separate mounting means to the support ring 40, as in Fig. 2 indicated.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP08150265A 2008-01-15 2008-01-15 Dispositif d'actionnement des aubes de guidage variables Withdrawn EP2080871A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP08150265A EP2080871A1 (fr) 2008-01-15 2008-01-15 Dispositif d'actionnement des aubes de guidage variables
EP09701799A EP2229508A1 (fr) 2008-01-15 2009-01-12 Dispositif de guidage pour le positionnement de pales
JP2010542606A JP5123400B2 (ja) 2008-01-15 2009-01-12 ガイド・デバイス
KR1020107016534A KR101265927B1 (ko) 2008-01-15 2009-01-12 터보기계 및 배기-가스 터보차저
PCT/EP2009/050258 WO2009090149A1 (fr) 2008-01-15 2009-01-12 Dispositif de guidage pour le positionnement de pales
CN2009801027723A CN101910566A (zh) 2008-01-15 2009-01-12 用于叶片调整的引导装置
US12/835,401 US8251647B2 (en) 2008-01-15 2010-07-13 Guide device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08150265A EP2080871A1 (fr) 2008-01-15 2008-01-15 Dispositif d'actionnement des aubes de guidage variables

Publications (1)

Publication Number Publication Date
EP2080871A1 true EP2080871A1 (fr) 2009-07-22

Family

ID=39537977

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08150265A Withdrawn EP2080871A1 (fr) 2008-01-15 2008-01-15 Dispositif d'actionnement des aubes de guidage variables
EP09701799A Withdrawn EP2229508A1 (fr) 2008-01-15 2009-01-12 Dispositif de guidage pour le positionnement de pales

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09701799A Withdrawn EP2229508A1 (fr) 2008-01-15 2009-01-12 Dispositif de guidage pour le positionnement de pales

Country Status (6)

Country Link
US (1) US8251647B2 (fr)
EP (2) EP2080871A1 (fr)
JP (1) JP5123400B2 (fr)
KR (1) KR101265927B1 (fr)
CN (1) CN101910566A (fr)
WO (1) WO2009090149A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8506233B2 (en) 2009-09-14 2013-08-13 Alstom Technology Ltd. Axial turbine and method for discharging a flow from an axial turbine
EP2781695A1 (fr) * 2013-03-22 2014-09-24 ABB Turbo Systems AG Aubes de guidage d'une turbine à gaz d'échappement

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102076638B1 (ko) * 2012-02-02 2020-05-19 보르그워너 인코퍼레이티드 가변 터빈 구조를 구비한 혼류 터보차저
US20140023502A1 (en) * 2012-07-20 2014-01-23 General Electric Company Variable vane assembly for turbine system
US9194249B2 (en) 2013-07-25 2015-11-24 Solar Turbines Incorporated Method for enhancing power of a gas turbine engine
GB201616108D0 (en) * 2016-09-22 2016-11-09 Rolls Royce Plc Gas turbine engine
US11339710B2 (en) 2018-05-09 2022-05-24 Feizal Alli Gaffoor Turbocharger
DE102021129534A1 (de) * 2021-11-12 2023-05-17 MTU Aero Engines AG Leitschaufelanordnung einer Strömungsmaschine und Verfahren zur Montage einer Leitschaufelanordnung

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3542484A (en) * 1968-08-19 1970-11-24 Gen Motors Corp Variable vanes
DE10013335A1 (de) * 2000-03-17 2001-09-20 Abb Turbo Systems Ag Baden Leitapparat für eine axial durchströmte Abgasturbine

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US3074689A (en) * 1960-06-06 1963-01-22 Chrysler Corp Adjustable nozzle ring support
US3747343A (en) * 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
US3817655A (en) * 1972-11-22 1974-06-18 Carrier Corp Stator blade mounting structure for turbomachines
US4003675A (en) * 1975-09-02 1977-01-18 Caterpillar Tractor Co. Actuating mechanism for gas turbine engine nozzles
US4497171A (en) * 1981-12-22 1985-02-05 The Garrett Corporation Combustion turbine engine
DE4213709A1 (de) * 1992-04-25 1993-10-28 Asea Brown Boveri Axialdurchströmte Turbine
DE19618314A1 (de) * 1996-05-08 1997-11-13 Asea Brown Boveri Abgasturbine eines Abgasturboladers
JP2002303147A (ja) * 2001-04-05 2002-10-18 Toyota Motor Corp 可変容量型ターボチャージャ
US7097420B2 (en) * 2004-04-14 2006-08-29 General Electric Company Methods and apparatus for assembling gas turbine engines
DE102004030798B4 (de) * 2004-06-25 2014-12-24 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine mit variabler Turbinengeometrie
JP4247214B2 (ja) 2004-10-29 2009-04-02 三菱重工業株式会社 排気タービン過給機
EP1669548A1 (fr) * 2004-12-08 2006-06-14 ABB Turbo Systems AG Système d'aubes de guidage réglable pour une turbine à gaz
GB2426555A (en) * 2005-05-28 2006-11-29 Siemens Ind Turbomachinery Ltd Turbocharger air intake

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3542484A (en) * 1968-08-19 1970-11-24 Gen Motors Corp Variable vanes
DE10013335A1 (de) * 2000-03-17 2001-09-20 Abb Turbo Systems Ag Baden Leitapparat für eine axial durchströmte Abgasturbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
R. H. KEMP; M. H. HIRSCHBERG; W. C. MORGAN: "Theoretical and Experimental Analysis of the Reduction of Rotor Blade Vibration in Turbomachinery Through the use of Modified Stator Vane Spacing", NACA TECHNICAL NOTE, 1958, pages 4374

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8506233B2 (en) 2009-09-14 2013-08-13 Alstom Technology Ltd. Axial turbine and method for discharging a flow from an axial turbine
DE102010044819B4 (de) 2009-09-14 2022-12-15 General Electric Technology Gmbh Axialturbine und ein Verfahren zum Abführen eines Stroms von einer Axialturbine
EP2781695A1 (fr) * 2013-03-22 2014-09-24 ABB Turbo Systems AG Aubes de guidage d'une turbine à gaz d'échappement

Also Published As

Publication number Publication date
KR20100095642A (ko) 2010-08-31
US20100278651A1 (en) 2010-11-04
US8251647B2 (en) 2012-08-28
WO2009090149A1 (fr) 2009-07-23
EP2229508A1 (fr) 2010-09-22
JP2011510207A (ja) 2011-03-31
CN101910566A (zh) 2010-12-08
KR101265927B1 (ko) 2013-05-20
JP5123400B2 (ja) 2013-01-23

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