EP2243932B1 - 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
EP2243932B1
EP2243932B1 EP10152861.0A EP10152861A EP2243932B1 EP 2243932 B1 EP2243932 B1 EP 2243932B1 EP 10152861 A EP10152861 A EP 10152861A EP 2243932 B1 EP2243932 B1 EP 2243932B1
Authority
EP
European Patent Office
Prior art keywords
guide
hub
guide blades
blade
guide blade
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.)
Expired - Lifetime
Application number
EP10152861.0A
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German (de)
English (en)
Other versions
EP2243932A3 (fr
EP2243932A2 (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 Energy Solutions SE
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Filing date
Publication date
Application filed by MAN Energy Solutions SE filed Critical MAN Energy Solutions 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 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.
  • For the given characteristic for example, of an exhaust gas turbocharger in connection with a piston engine of high specific power makes it difficult to provide the desired air supply for the entire operating range.
  • By opening the turbine cross-section with increasing load according to a given characteristic then the pressure increase can be limited so that at full load the purge air pressure and so that also adjust the ignition pressure and fuel consumption of the normal designed engine.
  • 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 area in the turbine at partial engine load, thereby increasing the air pressure in front of the cylinder.
  • the previously known axially flowed adjustable Turbinenleitapparat includes within the annular flow passage bounding walls on the one hand, the inner hub and on the other hand, the hub ring-shaped outer stator vane carrier, which is mounted in the Zuströmgephaseuse 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.
  • US 2,651,496A discloses a turbine having one of the compliant hub contour and compliant bearing of the vanes.
  • the compliant hub contour is provided by an inner ring attached to a flange.
  • the flange for the inner ring is connected to another flange by fastening screws.
  • DE 42 13 716 A1 discloses a nozzle of an axial turbine with adjustable vanes.
  • US 3,999,883 A and GB 878,988 A Further prior art is known.
  • 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 resilient, the flow losses through gaps between the Leitschaufel- and Zuströmgepuruse- or hub contours are reduced and also stresses the components of the adjustable nozzle, caused by sealing elements and thermal expansion of the components are avoided.
  • the resilient configuration of the bearing of the guide vanes in the guide vane carrier is achieved by means of a disc spring acting in the direction of the vane axes ensures that the head profile of a vane in each operating condition rests against the Zuströmgephaseusekontur, whereby kept the gap between these two components very low or completely avoided.
  • the yielding hub contour is designed in the form of an inner ring fitted in the hub contour, which in the pretensioned state bears against the foot profiles of the guide vanes, this inner ring is always in contact with the guide blade contours.
  • the inner ring is flanged to the hub such that it is movable in the radial direction of the inflow housing, that is to say in the direction of the guide blade axis, but is inserted into the hub contour in the axial direction of the inflow housing only with slight play.
  • mass flow losses are avoided.
  • the inner ring is provided for Monday with a slot, so that here also a thermal expansion is compensated.
  • the slot is according to the invention arranged so that it lies between two 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 fact that in addition the slot is covered by means of a sealing plate with respect to the hub interior on the inside, mass flow losses through the slot can be 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.
  • the inventive design of the diffuser of a generic axial flow machine an increased friction between the components is accepted, jamming of the mechanism, caused by different thermal expansions of the components is effectively prevented.
  • the material selection could be such that in the gray cast iron guide vanes made of a high temperature resistant material are stored in a ceramic vane carrier and sealed with their foot profiles against a likewise cast hub. At the same time, it is ensured that the gaps between the guide blade and the inlet housing or hub can be kept as low as possible, as a result of which the flow losses can be reduced to a minimum.
  • 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 guide blade 1, a blade pin 2 and a Schaufeldtehteller 3.
  • the blade pin 2 is rotatably mounted in a radial bearing bore of the annular vane support 7 and fixed in a known manner, for example by means of a screwed cap nut or the like on the vane support 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 Leitschaufeiblattes 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 into 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 is 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)

Claims (3)

  1. Turbomachine axiale,
    comportant un canal d'écoulement (20),
    comportant une tuyère de guidage dans le canal d'écoulement (20) comprenant un étage d'aubes de guidage variables (30),
    dans laquelle le canal d'écoulement (20) est délimité d'une part par un moyeu intérieur (21) et d'autre part par un support d'aube de guidage annulaire extérieur (7),
    dans laquelle les aubes de guidage comprennent une surface portante d'aube de guidage (1) avec un profilé de pied (31) et un profilé de tête (32), un point d'articulation d'aube (2), un plateau tournant d'aube de guidage (3) et un axe d'aube de guidage (A),
    dans laquelle les aubes de guidage sont d'un côté positionnées rotativement au niveau de leur profilé de tête (32) dans des alésages de palier radiaux du support d'aube de guidage annulaire (7) et d'un autre côté les profilés de pied (31) des aubes de guidage isolent de manière étanche contre le moyeu (21),
    dans laquelle le moyeu (21) est conçu au moins dans la zone d'étanchéité (23) du profilé de pied (31) des aubes de guidage (30) avec un contour de moyeu élastique, qui est conçu sous la forme d'une bague intérieure (9) pourvue d'une fente (10), adaptée au contour de moyen, laquelle s'appuie en l'état précontraint contre le profilé de pied (31) des aubes de guidage (30), et qui est fixée au moyen d'une bride (12) sur le moyen (21), de sorte qu'elle soit mobile dans la direction de l'axe d'aube de guidage (A) des aubes de guidage (30), néanmoins présente sur le contour du moyeu (21) dans la direction axiale du canal d'écoulement (20) uniquement un jeu minime, moyennant quoi un contact entre la bride (12) et la bague intérieure (9) est exclusivement denté, et
    dans laquelle le positionnement des aubes de guidage (30) dans la direction des axes d'aubes de guidage (A) a également une configuration élastique (4),
    caractérisée en ce que
    le positionnement des aubes de guidage (30) est configuré de manière élastique (4) au moyen respectivement d'une rondelle-ressort (4) agissant dans la direction des axes d'aubes directrices (A) et en ce que
    la fente (10) de la bague intérieure (9) est disposée de telle sorte qu'elle soit positionnée entre deux aubes de guidage (30) et ne sont pas balayée lors du mouvement de réglage de l'aube de guidage (30).
  2. Turbomachine axiale selon la revendication 1, caractérisée en ce que le contour intérieur du support d'aube de guidage annulaire (7), le moyeu (21), ainsi que les profilés de tête et de pied (31 et 32) des aubes de guidage (30) sont conçus en forme de bille afin d'améliorer de manière correspondante l'effet d'étanchéité.
  3. Turbomachine selon la revendication 1, caractérisée en ce que la fente (10) est recouverte au moyen d'une tôle d'étanchéité (11) par rapport à l'espace intérieur du moyeu (22).
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
EP01108009.0 Division 2001-03-29
EP01108009A Division EP1143111B8 (fr) 2000-04-04 2001-03-29 Turbomachine axiale avec des aubes de guidage variables

Publications (3)

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

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DE102005040574A1 (de) * 2005-08-26 2007-03-15 Rolls-Royce Deutschland Ltd & Co Kg Spaltkontrollvorrichtung für eine Gasturbine
DE102007021448B4 (de) * 2006-05-18 2012-06-28 Man Diesel & Turbo Se Leitapparat für einen Abgasturbolader einer mit Schweröl betriebenen Hubkolben-Brennkraftmaschine
CH698928B1 (de) * 2006-05-18 2009-12-15 Man Diesel Se Leitapparat für eine axial angeströmte Turbine eines Abgasturboladers.
CA2737516A1 (fr) 2008-09-18 2010-03-25 Siemens Aktiengesellschaft Procede, systeme et dispositif pour aubes directrices variables
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
EP4435235A1 (fr) * 2023-03-20 2024-09-25 General Electric Company Polska Sp. Z o.o Compresseur et moteur turboprop
US12221894B2 (en) 2023-03-20 2025-02-11 General Electric Company Polska Sp. Z O.O. Compressor with anti-ice inlet
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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Also Published As

Publication number Publication date
CN1316582A (zh) 2001-10-10
DE10016745B4 (de) 2005-05-19
EP1143111B8 (fr) 2010-05-19
EP1143111A3 (fr) 2003-05-07
CN1278019C (zh) 2006-10-04
US20010026758A1 (en) 2001-10-04
JP2001289004A (ja) 2001-10-19
EP1143111B1 (fr) 2010-03-17
KR100824894B1 (ko) 2008-04-23
DE50115388D1 (de) 2010-04-29
DE10016745A1 (de) 2001-10-18
EP2243932A3 (fr) 2011-01-26
EP1143111A2 (fr) 2001-10-10
US6547521B2 (en) 2003-04-15
EP2243932A2 (fr) 2010-10-27
KR20010095249A (ko) 2001-11-03

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