EP2243932A2 - Turbomachine axiale avec une tuyère de guidage comprenant un étage d'aubes de guidage variables - Google Patents

Turbomachine axiale avec une tuyère de guidage comprenant un étage d'aubes de guidage variables Download PDF

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Publication number
EP2243932A2
EP2243932A2 EP10152861A EP10152861A EP2243932A2 EP 2243932 A2 EP2243932 A2 EP 2243932A2 EP 10152861 A EP10152861 A EP 10152861A EP 10152861 A EP10152861 A EP 10152861A EP 2243932 A2 EP2243932 A2 EP 2243932A2
Authority
EP
European Patent Office
Prior art keywords
hub
guide vanes
guide
exhaust gas
gas turbocharger
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.)
Granted
Application number
EP10152861A
Other languages
German (de)
English (en)
Other versions
EP2243932B1 (fr
EP2243932A3 (fr
Inventor
Klaus Dr. Bartholomä
Karl Heinz Schrott
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.)
Everllence SE
Original Assignee
MAN Diesel SE
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 MAN Diesel SE filed Critical MAN Diesel SE
Publication of EP2243932A2 publication Critical patent/EP2243932A2/fr
Publication of EP2243932A3 publication Critical patent/EP2243932A3/fr
Application granted granted Critical
Publication of EP2243932B1 publication Critical patent/EP2243932B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • 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 an exhaust gas turbocharger turbine with a number of adjustable guide vanes comprehensive in the flow channel, which is bounded on the one hand by an inner hub and the other by an outer vane support, wherein the vanes are rotatably mounted on the one hand in radial bearing bores of the annular vane support and on the other hand with seal their head profile against the guide vane, and with their foot profile against the hub, so the guide vanes are mounted on one side.
  • Adjustable, in particular turbine nozzles are known to be used in turbine and turbocharger construction to better adapt the turbine during operation to the respective operating state.
  • the boost pressure and thus the supply of air for a given load point can be changed within certain limits.
  • the pressure increase can be limited so that set at full load, the purge air pressure and thus the ignition pressure and fuel consumption of the engine normally designed.
  • the efficiency of the turbine with an adjustable turbine nozzle in particular during operation away from the design point, be raised or lowered.
  • adjustable turbine nozzles have a plurality of rotatable about an axis arranged vanes, which are articulated via levers and collars.
  • adjustable turbine nozzles for axially and radially traversed turbines. While the radially flowed adjustable turbine nozzle can be relatively simple (see, for example DE 42 18 229 C1 ), the axially flowed through is much more expensive to realize, since in particular the hub and Zuströmgepurtur spherical, ie at least curved must be designed. This is necessary to produce a uniform radial gap at all blade positions toward the hub and inflator housing contours.
  • a generic axial flow machine, in particular axial flow turbine shows the DE 42 13 709 A1 .
  • the adjustable turbine nozzle offers the possibility of reducing the flow cross-section in the turbine at partial load of the engine and thereby raising the air pressure in front of the cylinder.
  • the known axially flowed adjustable turbine nozzle comprises within the annular flow passage defining walls on the one hand, the inner hub and on the other hand, the hub ring-shaped outer stator blade carrier, which is mounted in the inlet housing of the turbine.
  • vanes do not jam during "hot” operation, they usually need to be installed with adequate clearance.
  • the resulting slit flows at the top and bottom of the vanes can interfere with the main flow in the duct.
  • the invention has the object of developing an exhaust gas turbocharger such that the components of the diffuser are both smoothly actuated, and allow only small gap flows.
  • both above-mentioned requirements should be combined in a new axial flow machine.
  • the hub is designed at least in the sealing region of theticianprofiles the vanes with a resilient hub contour and the one-sided storage of the vanes in the vane support in the direction of the vanes is also designed compliant, the flow losses through gaps between the Leitschaufel- and the Zuströmgepatuse- or hub contours be reduced and also to avoid distortion of the components of the adjustable nozzle, caused by sealing elements and thermal expansion of the components.
  • the inner ring is provided for Monday with a slot, so that a thermal expansion is compensated here as well.
  • the slot is arranged so that it lies between two guide vanes and is not swept by the blade contour during an adjustment process, so that the losses caused by the slot can be minimized.
  • the inner ring is flanged to the hub so that it is movable in the radial direction of the Zuströmgeophuses, ie in the direction of the vane axis, in the axial direction of the Zuströmgepatuse but only with little play is inserted into the hub contour. By this measure again mass flow losses are avoided.
  • the inner contour of the annular guide carrier, the hub, as well as the head and foot profiles of the vanes are designed to improve the sealing effect according to spherical.
  • FIG. 1 a partial longitudinal section through an exhaust gas turbocharger.
  • An axial flow-through, annular channel 20 of an axial turbine is limited on the one hand by an inner hub 21 and on the other by an annular guide vane carrier 7 together with Zuströmgephaseuse 8.
  • the vane support 7 is mounted in a manner not described in detail in the Zuströmgephase 8.
  • the adjustable guide vanes 30 each comprise a stator blade 1, a blade journal 2 and a blade turntable 3.
  • the blade journal 2 is rotatably mounted in a radial bearing bore of the annular guide blade carrier 7 and fixed in a known manner, for example by means of a screwed crown nut or the like on the guide vane carrier 7.
  • an articulated lever 5 is rotationally fixed by means of a key on the extended pin 2 of the guide vane 30.
  • the articulated lever 5 is contacted with the blade journal 2 and the guide blade carrier 7 with the interposition of a plate spring 4, so that the articulation lever 5 is supported against the guide blade carrier 7.
  • the plate spring 4 exerts on the blade journal 2 a Biasing force, by which the base profile 31, ie the lower contour of the vane blade 1 is pressed against the outer surface of the hub 21, so the base profile 31 of the vane 30 is at the stop with the hub 21 and thus seals against the contour of the hub 21.
  • the blade journal 2 in the bearing bore of the guide blade carrier 7 almost free of play, but still clamped against thermal expansion in the direction of the axis A of the vane 30 elastic and vibration damping.
  • the blade turntable 3 seals the channel 20 against the bearing bore of the guide blade carrier 7.
  • the articulated lever 5 is movable in a known manner via a collar 6 by means not shown actuating means.
  • the housing contour of the hub 21 is designed at least partially spherical with the inclusion of a hollow or inner space 22.
  • an inner ring 9 is fitted in the Nabekontur, which is supported in the prestressed state against the base profile 31 of the vane 30 and is secured by a flange 12 to the hub 21 so that it in the direction of the axis
  • the guide vane 30 is movable, it has only slight play in the contour of the hub 21, that is to say in the axial direction of the channel 20.
  • the inner ring 9 itself is provided with a slot 10 which is arranged so that it lies between two guide vanes and is not swept by the blade contour during the adjustment process. In order to prevent mass flow losses through the slot 10, it is covered by the hollow or inner space 22 of the hub 21 seen with a sealing plate 11.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10152861.0A 2000-04-04 2001-03-29 Turbomachine axiale avec une tuyère de guidage comprenant un étage d'aubes de guidage variables Expired - Lifetime EP2243932B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10016745A DE10016745B4 (de) 2000-04-04 2000-04-04 Axialströmungsmaschine mit einem eine Reihe von verstellbaren Leitschaufeln umfassenden Leitapparat
EP01108009A EP1143111B8 (fr) 2000-04-04 2001-03-29 Turbomachine axiale avec des aubes de guidage variables

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP01108009A Division EP1143111B8 (fr) 2000-04-04 2001-03-29 Turbomachine axiale avec des aubes de guidage variables
EP01108009.0 Division 2001-03-29

Publications (3)

Publication Number Publication Date
EP2243932A2 true EP2243932A2 (fr) 2010-10-27
EP2243932A3 EP2243932A3 (fr) 2011-01-26
EP2243932B1 EP2243932B1 (fr) 2019-03-13

Family

ID=7637566

Family Applications (2)

Application Number Title Priority Date Filing Date
EP01108009A Expired - Lifetime EP1143111B8 (fr) 2000-04-04 2001-03-29 Turbomachine axiale avec des aubes de guidage variables
EP10152861.0A Expired - Lifetime EP2243932B1 (fr) 2000-04-04 2001-03-29 Turbomachine axiale avec une tuyère de guidage comprenant un étage d'aubes de guidage variables

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP01108009A Expired - Lifetime EP1143111B8 (fr) 2000-04-04 2001-03-29 Turbomachine axiale avec des aubes de guidage variables

Country Status (6)

Country Link
US (1) US6547521B2 (fr)
EP (2) EP1143111B8 (fr)
JP (1) JP2001289004A (fr)
KR (1) KR100824894B1 (fr)
CN (1) CN1278019C (fr)
DE (2) DE10016745B4 (fr)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005040574A1 (de) * 2005-08-26 2007-03-15 Rolls-Royce Deutschland Ltd & Co Kg Spaltkontrollvorrichtung für eine Gasturbine
CH698928B1 (de) * 2006-05-18 2009-12-15 Man Diesel Se Leitapparat für eine axial angeströmte Turbine eines Abgasturboladers.
DE102007021448B4 (de) * 2006-05-18 2012-06-28 Man Diesel & Turbo Se Leitapparat für einen Abgasturbolader einer mit Schweröl betriebenen Hubkolben-Brennkraftmaschine
CN102159794B (zh) * 2008-09-18 2015-04-15 西门子公司 用于可变导向叶片的方法、系统和装置
US8668445B2 (en) * 2010-10-15 2014-03-11 General Electric Company Variable turbine nozzle system
CN102606223B (zh) * 2011-01-24 2014-12-17 中国石油化工集团公司 一种烟气轮机
DE102011119879A1 (de) * 2011-12-01 2013-06-06 Ihi Charging Systems International Gmbh Fluidenergiemaschine, insbesondere für einen Abgasturbolader eines Kraftwagens
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
DE102018101527A1 (de) 2018-01-24 2019-07-25 Man Energy Solutions Se Axialströmungsmaschine
CN112989720B (zh) * 2021-03-04 2022-05-06 上海交通大学 轴流压气机悬臂静子叶片优化轮毂径向间隙实现方法
US12416262B2 (en) 2023-02-17 2025-09-16 General Electric Company Reverse flow gas turbine engine having electric machine
US12221894B2 (en) 2023-03-20 2025-02-11 General Electric Company Polska Sp. Z O.O. Compressor with anti-ice inlet
EP4435235A1 (fr) * 2023-03-20 2024-09-25 General Electric Company Polska Sp. Z o.o Compresseur et moteur turboprop
FR3163396A1 (fr) 2024-06-12 2025-12-19 Safran Aircraft Engines Mecanisme de commande d’aubes de stator de turbomachine avec au moins un raidisseur

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BE514728A (fr) * 1951-10-10
CH360074A (de) * 1957-10-31 1962-02-15 Maschf Augsburg Nuernberg Ag Leitapparat mit im Betrieb verstellbaren Schaufeln, besonders für Gasturbinen
US3542484A (en) * 1968-08-19 1970-11-24 Gen Motors Corp Variable vanes
FR2030895A5 (fr) * 1969-05-23 1970-11-13 Motoren Turbinen Union
US3999883A (en) * 1975-07-02 1976-12-28 General Motors Corporation Variable turbomachine stator
DE2740192C2 (de) 1977-09-07 1981-11-12 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Spaltdichtung für eine um ihre Längsachse verstellbare, axial umströmte Leitschaufel einer Strömungsmaschine
DE2931766C2 (de) * 1979-08-04 1982-08-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Dichtungseinrichtung für die freien Schaufelenden eines Verstell-Leitapparates einer Gasturbine
GB2210935B (en) * 1987-10-10 1992-05-27 Rolls Royce Plc Variable stator vane assembly
GB8914577D0 (en) * 1989-06-24 1989-08-16 Ici Plc Catalysts
DE4017861A1 (de) * 1990-06-02 1991-12-05 Mtu Muenchen Gmbh Leitkranz fuer eine gasturbine
DE4213716A1 (de) * 1992-04-25 1993-10-28 Asea Brown Boveri Axialdurchströmte Turbine
DE4213709A1 (de) 1992-04-25 1993-10-28 Asea Brown Boveri Axialdurchströmte Turbine
DE4218229C1 (en) 1992-06-03 1993-03-04 Man B & W Diesel Ag, 8900 Augsburg, De Turbocharger with radial flow through impeller - has blade retaining recesses, into which blades are insertable after axial shift of adjuster
DE4237031C1 (de) 1992-11-03 1994-02-10 Mtu Muenchen Gmbh Verstellbare Leitschaufel
US5672047A (en) * 1995-04-12 1997-09-30 Dresser-Rand Company Adjustable stator vanes for turbomachinery
JPH09203371A (ja) * 1996-01-26 1997-08-05 Hitachi Ltd 土砂摩耗対応水力機器
FR2775731B1 (fr) * 1998-03-05 2000-04-07 Snecma Etage circulaire d'aubes aux extremites interieures unies par un anneau de liaison

Also Published As

Publication number Publication date
EP2243932B1 (fr) 2019-03-13
EP1143111A2 (fr) 2001-10-10
CN1316582A (zh) 2001-10-10
EP1143111A3 (fr) 2003-05-07
JP2001289004A (ja) 2001-10-19
DE50115388D1 (de) 2010-04-29
DE10016745B4 (de) 2005-05-19
KR100824894B1 (ko) 2008-04-23
EP1143111B8 (fr) 2010-05-19
CN1278019C (zh) 2006-10-04
EP1143111B1 (fr) 2010-03-17
US20010026758A1 (en) 2001-10-04
KR20010095249A (ko) 2001-11-03
DE10016745A1 (de) 2001-10-18
EP2243932A3 (fr) 2011-01-26
US6547521B2 (en) 2003-04-15

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