EP1111196B1 - Système d'aubes de guidage variables pour la turbine d'une turbosoufflante - Google Patents

Système d'aubes de guidage variables pour la turbine d'une turbosoufflante Download PDF

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Publication number
EP1111196B1
EP1111196B1 EP00106218A EP00106218A EP1111196B1 EP 1111196 B1 EP1111196 B1 EP 1111196B1 EP 00106218 A EP00106218 A EP 00106218A EP 00106218 A EP00106218 A EP 00106218A EP 1111196 B1 EP1111196 B1 EP 1111196B1
Authority
EP
European Patent Office
Prior art keywords
annular piston
exhaust gas
gas turbine
guide
pressure
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
EP00106218A
Other languages
German (de)
English (en)
Other versions
EP1111196A3 (fr
EP1111196A2 (fr
Inventor
Helmut Daudel
Wolfgang Erdmann
Peter Fledersbacher
Carsten Funke
Paul Löffler
Siegfried Sumser
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.)
Mercedes Benz Group AG
Original Assignee
DaimlerChrysler 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 DaimlerChrysler AG filed Critical DaimlerChrysler AG
Publication of EP1111196A2 publication Critical patent/EP1111196A2/fr
Publication of EP1111196A3 publication Critical patent/EP1111196A3/fr
Application granted granted Critical
Publication of EP1111196B1 publication Critical patent/EP1111196B1/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
    • 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
    • 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
    • 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
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line

Definitions

  • the invention relates to an exhaust gas turbine of an exhaust gas turbocharger for an internal combustion engine according to the closer defined in the preamble of claim 1.
  • a generic exhaust gas turbine is also known from DE 195 43 190 C2.
  • adjustable blocking bodies are provided in an annular nozzle in which a variable guide grid is arranged, which are intended to increase the operational reliability of the exhaust gas turbine when operated as an engine brake.
  • a variably adjustable guide vane grille of a turbine of an exhaust gas turbocharger wherein a sealing element is provided in each case in a pressure chamber per guide vane.
  • the sealing elements are designed as a sealing cup and can be pressed sealingly against the free blade end. In this way, the Leitgitterspalt to be completely sealed at the blade ends.
  • the disadvantage here is that according to the number The guide vanes a large number of sealing elements is required, which means a considerable effort and a susceptibility to operation.
  • higher adjusting forces must be applied.
  • the present invention is therefore based on the object to provide an exhaust gas turbine of the aforementioned type, wherein the efficiency of the exhaust gas turbine or the exhaust gas turbocharger is always optimally adjustable depending on the operating condition of the internal combustion engine, in particular an improvement in the acceleration behavior of the turbine during engine braking. and the drive mode of operation is achieved even at low engine speeds and a rapid build-up of boost pressure and thus a faster build-up of a high braking or drive torque, and at the same time avoid overloading the exhaust turbine or the turbocharger under extreme conditions becomes.
  • the efficiency of the exhaust gas turbine and thus also of the exhaust gas turbocharger can always be optimally adapted to the respective operating state of the internal combustion engine or adjust it.
  • the gap can be reduced to zero, which takes place advantageously by a corresponding clamping, so that even at low engine speeds an improvement in the acceleration behavior of the exhaust gas turbine during engine braking occurs.
  • a faster build up of the boost pressure for the compressor and thus a faster construction of a high braking torque is achieved, because gap losses are avoided in this way.
  • the exhaust gas turbine can be controlled in their efficiency in a simple way.
  • a particular advantage of the change or adjustment of the gap according to the invention lies in the fact that the exhaust gas turbine can be driven very close to its speed limit or the exhaust gas turbine can be designed to be correspondingly high.
  • An exhaust gas turbocharger has an exhaust gas turbine 1 arranged in the exhaust gas flow, which is connected to a compressor 3 via a drive shaft 2.
  • the compressor 3 is located in a leading to an internal combustion engine 4 intake 5 and leads to the internal combustion engine in this way pre-compressed air.
  • the exhaust gas turbine 1 is located in an exhaust pipe 6.
  • the exhaust gas turbine 1 has on the input side a spiral flow channel 7, from where the exhaust gas via an annular nozzle 8 leads to an impeller of a turbine 9, which is arranged on the drive shaft 2.
  • the flow channel 7, the annular nozzle 8 and the turbine 9 are located in a common housing 10.
  • the annular nozzle 8 is limited by axial walls.
  • the guide grid 11 and the guide vanes 12 are in a known manner by a Leitgitterverstell Rhein 13 so adjustable that the effective flow cross section of the annular nozzle 8 between a maximum open position and a nearly closed Adjustable position or is adjustable.
  • an annular piston 14 On the side facing away from the Leitgitterverstell Surprise 13 is provided as a wall in the adjustment of the vanes 12, an annular piston 14 in the form of a disc.
  • a pressure chamber 15 On the side facing away from the vanes 12 side of the annular piston 14 is a pressure chamber 15, which communicates via a pressure connection 16 with a pressure supply line 17.
  • a pressure accumulator 18 In general, one will fall back as the pressure medium on the Preßluftbordnetz, if this is available. However, it is of course also possible for this purpose to provide its own printing system with a pressure accumulator 18, wherein, of course, combinations are possible.
  • the gap between the guide grid 11 and vanes 12 and the adjacent walls should be minimized or best eliminated completely.
  • a complete elimination has not been readily possible in the prior art for reasons of thermal expansion of the vanes 12 and the operation of the Leitgitterverstell Surprise 13.
  • the annular piston 14 which now forms the axial wall in the movement or adjustment of the guide vanes 12, the gap between the guide vanes 12 and the adjacent wall can now be set variably.
  • the pressure for the adjustment of the annular piston 14 via the pressure supply line 17 and the pressure accumulator 18 (or the Preßluftbordnetz), 19 corresponding pressure changes or pressure modulations can be performed via a pressure regulating or shut-off device.
  • the pressure control device 19 is controlled by a motor control device 21 via a control line 20.
  • the pressurization can also take place via a branch line 22, which is connectable to the pressure port 16 via a not-shown 3-way valve 31 in the pressure supply line 17 (dashed line in Fig. 2).
  • the accumulator 18 is charged by the exhaust pressure in the exhaust pipe 6 via a check valve 23.
  • the loading of the pressure accumulator or the pressure chamber 15 of the annular piston 14 can also take place via a motor compressor 24.
  • the gap adjustment is carried out in conjunction with the control device 21 and the control line 20 via the setting of the control device 19. Intermediate sizes of the gap and also the level of the contact pressure of the annular piston 14 to the guide vanes 12 is realized by a pressure modulation via the control device 19. If required, the annular piston 14 can also be configured with a spring 25 as a spring device, which is preferably arranged in the pressure chamber 15, which would ensure a neutral position or an output gap.
  • axially directed pins 26 may be provided which engage in holes on the back of the annular piston 14, so that tilting of the annular piston 14 is avoided, which would be disadvantageous in terms of the two-sided support of the guide vanes 12 via the pin bearings 29 ,
  • the annular piston 14 has a very thin-walled thickness, in particular in the middle region, and has no guide pins 26. In this way you get a simplified Construction.
  • the annular piston 14 in this case no longer serves as a second bearing point for the guide vanes 11. It is provided in particular for smaller exhaust forces acting on the guide vanes 11. A tilting moment of the guide vanes 11 can be neutralized by the clamping due to the adjacent annular piston 14.
  • the annular piston 14 is particularly greatly tapered in the central region, so that it can create elastic by the high pressure forces in the piston chamber 15 to the vanes 11 and thus securely clamps all vanes 11 in the respective position.
  • the piston ring 14 in this embodiment can also be operated by the compressed air port 16 via the three-way valve 31 in the manner as has been explained in the first embodiment.
  • annular piston 14 is described, which is provided with a damping device.
  • Ring piston 14 and damping ring 33 are pressed apart by a spring means 34 and the gap 35 between the annular piston 14 and the damping ring 33 fills via one or more throttle bores 36 with compressed air from the piston chamber 15th
  • the damping of the annular piston 14 is thus achieved in the following manner: In pulsations of the exhaust gas flowing through the exhaust gas turbine, the piston ring 14 can only perform an inhibited or delayed movement axially to the turbine wheel. Thus, vibrations are prevented, because the throttle bores 36, which lead into the intermediate space 35, have only such a small diameter that the pressure medium can escape only very slowly from the intermediate space 35.
  • each of the bearing pins 29 is not stored in the annular piston 14, but in the underlying fixed housing 10th the turbine.
  • located on a radially outwardly projecting shoulder 37 of the annular piston 14 each have a through hole 38 in the region of the guide vanes 12, through which the bearing pin 29 pushed through each with play and stored in a bearing bore 39 located behind the housing 10.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Claims (6)

  1. Turbine d'un turbocompresseur à gaz d'échappement pour un moteur thermique, comportant un rotor agencé dans un boîtier et au moins un canal d'écoulement (7) entourant le rotor et présentant une buse annulaire (8) qui débouche vers le rotor et dans laquelle est agencée au moins une grille directrice variable (11) comprenant des aubes directrices (12) et des canaux de grille directrice, la section d'écoulement efficace de la buse annulaire (8) étant réglable par la grille directrice (11) via un dispositif de positionnement (13) pour la grille directrice, un dispositif de réglage (14, 15, 16, 17) étant prévu qui règle la largeur de l'intervalle entre la grille directrice (11) et les portions de paroi de boîtier (10) qui entourent la grille directrice (11) entre un intervalle maximal et un intervalle nul, et une partie au moins des portions de paroi de boîtier qui se trouvent dans la zone de la grille directrice (11) est réalisée sous forme de piston annulaire (14) qui comprend une chambre sous pression (15), par alimentation en pression de laquelle le piston annulaire (14) est susceptible d'être pressé contre les aubes directrices (12) de la grille directrice (11),
    caractérisée en ce qu'une bague d'amortissement étanchée (33) se trouve à l'intérieur du piston annulaire (14), le piston annulaire (14) et la bague d'amortissement (33) étant écartés par un dispositif à ressort (34), et l'espace intermédiaire (35) entre le piston annulaire (14) et la bague d'amortissement (33) étant relié à la chambre (15) du piston via un ou plusieurs perçages d'étranglement (36).
  2. Turbine à gaz d'échappement selon la revendication 1, caractérisée en ce que la chambre sous pression (15) du piston annulaire (14) est reliée à un dispositif de régulation de pression, et en ce que le dispositif de régulation de pression (19) est relié via une conduite de commande (20) à un dispositif de régulation de moteur (21) pour engendrer des modulations de pression.
  3. Turbine à gaz d'échappement selon l'une ou l'autre des revendications 1 et 2, caractérisée en ce qu'au moins sur le côté tourné vers les aubes directrices (12), le piston annulaire (14) est réalisé élastique ou est pourvu d'un recouvrement élastique (27).
  4. Turbine à gaz d'échappement selon la revendication 3, caractérisée en ce que le piston annulaire (14) est réalisé avec une paroi mince au moins dans sa zone centrale.
  5. Turbine à gaz d'échappement selon l'une des revendications 1 à 4, caractérisée en ce que sur le côté détourné du dispositif de positionnement (13) pour la grille directrice, les aubes directrices (12) sont pourvues de paliers à tiges (29) qui sont enfichés à travers des perçages (38) dans un talon (37) du piston annulaire (14) et qui sont montés dans des perçages de montage (39) dans le boîtier (10).
  6. Turbine à gaz d'échappement selon la revendication 5, caractérisée en ce que le talon (37) du piston annulaire (14) présente une épaisseur de paroi inférieure à celle du piston annulaire (14).
EP00106218A 1999-12-21 2000-03-22 Système d'aubes de guidage variables pour la turbine d'une turbosoufflante Expired - Lifetime EP1111196B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19961613 1999-12-21
DE19961613A DE19961613A1 (de) 1999-12-21 1999-12-21 Abgasturbine eines Abgasturboladers für eine Brennkraftmaschine

Publications (3)

Publication Number Publication Date
EP1111196A2 EP1111196A2 (fr) 2001-06-27
EP1111196A3 EP1111196A3 (fr) 2002-07-24
EP1111196B1 true EP1111196B1 (fr) 2004-04-28

Family

ID=7933528

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00106218A Expired - Lifetime EP1111196B1 (fr) 1999-12-21 2000-03-22 Système d'aubes de guidage variables pour la turbine d'une turbosoufflante

Country Status (3)

Country Link
US (1) US6314736B1 (fr)
EP (1) EP1111196B1 (fr)
DE (2) DE19961613A1 (fr)

Cited By (1)

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DE102011121394A1 (de) 2011-12-17 2013-06-20 Ihi Charging Systems International Gmbh Verstellbarer Leitapparat für eine Turbine eines Abgasturboladers, Turbine für einen Abgasturboladerund Abgasturbolader

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US6647724B1 (en) 2002-07-30 2003-11-18 Honeywell International Inc. Electric boost and/or generator
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US11047256B2 (en) * 2016-11-10 2021-06-29 Ihi Corporation Variable nozzle unit and turbocharger
CN109983204B (zh) 2016-11-18 2021-11-23 液化空气(中国)投资有限公司 涡轮膨胀机的低摩擦入口喷嘴
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DE102011121394A1 (de) 2011-12-17 2013-06-20 Ihi Charging Systems International Gmbh Verstellbarer Leitapparat für eine Turbine eines Abgasturboladers, Turbine für einen Abgasturboladerund Abgasturbolader

Also Published As

Publication number Publication date
EP1111196A3 (fr) 2002-07-24
DE50006238D1 (de) 2004-06-03
DE19961613A1 (de) 2001-07-19
US6314736B1 (en) 2001-11-13
EP1111196A2 (fr) 2001-06-27

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