EP1337739B1 - Abgasturbolader mit variabler geometrie und einem ringschieber - Google Patents

Abgasturbolader mit variabler geometrie und einem ringschieber Download PDF

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Publication number
EP1337739B1
EP1337739B1 EP00985372A EP00985372A EP1337739B1 EP 1337739 B1 EP1337739 B1 EP 1337739B1 EP 00985372 A EP00985372 A EP 00985372A EP 00985372 A EP00985372 A EP 00985372A EP 1337739 B1 EP1337739 B1 EP 1337739B1
Authority
EP
European Patent Office
Prior art keywords
piston
turbine
housing
vanes
turbine wheel
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
EP00985372A
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English (en)
French (fr)
Other versions
EP1337739A1 (de
Inventor
Jean-Luc Hubert Honeywell Garrett SA PERRIN
Olivier Honeywell Garrett SA ESPASA
Marylène Honeywell Garrett SA RUFFINONI
Alain René Honeywell Garrett SA LOMBARD
Philippe Joseph Honeywell Garrett SA MULLER
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.)
Garrett Motion France SAS
Original Assignee
Honeywell Garrett SA
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Filing date
Publication date
Application filed by Honeywell Garrett SA filed Critical Honeywell Garrett SA
Publication of EP1337739A1 publication Critical patent/EP1337739A1/de
Application granted granted Critical
Publication of EP1337739B1 publication Critical patent/EP1337739B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • 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 present invention generally relates to variable geometry turbochargers. More particularly, it relates to a turbocharger having a sliding piston which creates a variable nozzle turbine inlet with fins extending across the nozzle in a closed position of the piston.
  • High efficiency turbochargers employ variable geometry systems for the turbine inlet nozzles to increase performance and aerodynamic efficiency.
  • the variable geometry systems for turbochargers are of two types, namely with pivoting vanes and piston.
  • the swivel wing type illustrated for example by US Patent No. 5,947,681 entitled “Pressure Balanced Dual Axle Variable Nozzle Turbocharger”
  • the piston type which is illustrated for example by US Pat. Nos. 5,214,920 and 5,231,831 both entitled “Turbocharger Apparatus” and US Patent No.
  • 5,441,383 entitled “Variable Exhaust Driven Turbochargers” employs a piston. or a cylindrical wall that is concentrically movable to the axis rotation of the turbine to reduce the section of the nozzle inlet.
  • the piston-type variable geometry turbocharger includes fins having a fixed angle of attack relative to the airflow, which are mounted on the piston or on a fixed nozzle wall opposite of the piston and which are received in grooves in the opposite surface during the movement of the piston.
  • a turbocharger utilizing the present invention comprises a turbine nozzle variable geometry turbocharger comprising a turbine body which receives the exhaust gas from an exhaust manifold of an internal combustion engine at an inlet and which has a discharge outlet, a compressor body having an air inlet and a first volute, and a central body placed between the turbine body and the compressor body; a turbine wheel mounted in the turbine body for extracting energy from the exhaust gas, said turbine wheel coupled to a shaft extending from the turbine body and passing through a shaft bore of the central body; a bearing mounted in the shaft bore of the central body, said bearing supporting the shaft for rotational movement; a compressor wheel coupled to the shaft, opposite the turbine wheel, and contained in the body of compressor; a substantially cylindrical piston concentric with the turbine wheel and movable parallel to the axis of rotation of the turbine wheel; the piston having a radial surface; a thermal shield taken at its outer circumference between the turbine body and the central body and extending radially inwards towards the axis of rotation, the said heat shield further having
  • FIG. 1 shows an embodiment of the invention for a turbocharger 10 which comprises a turbine body 12, a central body 14 and a compressor body 16.
  • a turbine wheel 18 is coupled by a shaft 20 to a wheel
  • the turbine wheel converts the energy of the exhaust gases of an internal combustion engine fed through an exhaust manifold (not shown) to a volute 24 in the turbine body.
  • the exhaust gas expands in the turbine and exits the turbine body through an outlet 26.
  • the compressor body includes an inlet 28 and an outlet volute 30.
  • a backplate 30 is connected by bolts 34 to the compressor body.
  • the back plate is itself fixed to the central body by means of bolts (not shown) or integrally cast from the central body.
  • a V-clamp 40 and alignment pins 42 connect the turbine body to the central body.
  • a bearing 50 mounted in the bore 52 of the central body supports the rotating shaft.
  • a sleeve 58 is held between the abutment surface and the compressor wheel.
  • a rotary seal 60 such as a piston ring, provides a seal between the sleeve and the back plate.
  • the variable geometry mechanism of the present invention comprises a substantially cylindrical piston 70 received in the turbine body concentrically aligned with the axis of rotation of the turbine.
  • the piston is longitudinally displaceable via a spider 72, having three branches in the embodiment shown, which is attached to the piston and attached to an operating rod 74.
  • the operating rod is received in a sleeve 76 which crosses the turbine body and is connected to an actuator 77.
  • the actuator is mounted on bosses of the turbine body via a support 78.
  • the piston slides in the turbine body via a low-friction insert 82.
  • a cylindrical seal 84 is inserted between the piston and the insert.
  • the piston is movable from a closed position shown in Fig. 1, wherein the section of the turbine inlet nozzle from the volute 24 is substantially reduced. In a fully open position, a radial projection 86 of the piston abuts against a face 88 of the insert to limit the displacement of the piston.
  • Jet vanes 90 extend from a heat shield 92. In the closed position of the piston, the vanes are in contact with the face of the radial projection of the piston.
  • the outer periphery of the heat shield is held between the turbine body and the central body.
  • the shield is configured to enter the turbine body cavity from the interface between the central body and the turbine body and constitutes an interior wall for the inlet nozzle of the turbine.
  • Figure 2 shows the turbocharger of Figure 1 when the piston 70 is in the open position.
  • An open annular channel 94 is created between the fins and the face of the radial projection.
  • the flow of exhaust gas through the fins and the annular channel which constitutes the open nozzle is stabilized in the direction by the fins. Modulation of the nozzle flow can be effected by positioning the piston at desired points between the fully open position and the fully closed position.
  • the piston operating system in the embodiment shown, is a pneumatic actuator 77 fixed to a support 78 as shown in FIGS. 1 and 2.
  • Fig. 3 shows a second embodiment of the invention incorporating a piston 70a which is made from a sheet of metal or by casting a thin wall having a substantially U-shaped cross-section so as to comprise an outer ring. 94 parallel to the direction of translation of the piston and an inner ring 96 extending to an attachment to a plate 98 for connection to the operating rod 74.
  • the outer ring of the piston is received in a groove 100 of the turbine body, and the ring The interior is closely received by the inner circumferential wall of the outlet of the turbine body, which creates a seal with offset seals for the piston.
  • the U-shaped piston core contacts the fins to define the minimum section nozzle.
  • FIG. 4 represents the embodiment of FIG. 3, the piston being in the open position and the U core being remote from the fins to obtain the free annular space (94) previously described for the open nozzle producing a maximum section. nozzle inlet.
  • the contact of the edge of the outer ring 84 with the end of the groove 100 or, alternatively, the contact of the core of the U with the adjacent face 88a of the turbine body limits the stroke of the piston.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Claims (2)

  1. Turbokompressor (10) mit variabler Geometrie des Turbinenrohres, umfassend
    einen Turbinenkörper (12) zur Aufnahme der Abgase aus einem Abgassammler eines internen Verbrennungsmotors an einem Einlass (24) und mit einer Austrittsöffnung für Abgase (26), einem Kompressorkörper (16) mit einem Lufteinlass (28) sowie einer ersten Spirale (30) und einem Zentralkörper (14) zwischen dem Turbinen- und dem Kompressorkörper;
    ein Turbinenrad (18), das im Turbinenkörper angebracht ist und die Energie aus den Abgasen extrahiert, wobei dieses Turbinenrad an eine Welle (20) gekoppelt ist, die aus dem Turbinenkörper heraus- und in eine Bohrung (52) der Welle des Zentralkörpers übergeht;
    ein Lager (50), das in der Bohrung der Welle des Zentralkörpers angebracht ist, wobei dieses Lager die Welle in Rotation unterstützt;
    ein Kompressorrad (22), das an die Welle gekoppelt ist, gegenüber des Turbinenrads und innerhalb des Kompressorkörpers;
    einen im Wesentlichen zylindrischen Kolben (70), konzentrisch zum Turbinenrad (18) und parallel zur Rotationsachse des Turbinenrads verschiebbar; wobei der Kolben eine radiale Oberfläche aufweist;
    einen thermischen Schutzschild (92), der mit seinem äußeren Umfang zwischen dem Turbinenkörper und dem Zentralkörper eingegriffen ist und sich radial nach innen zur Rotationsachse hin erstreckt, wobei der thermische Schutzschild darüber hinaus eine Vielzahl von Turbinenschaufeln aufweist (90), die im Wesentlichen parallel zur Rotationsachse sind, und
    Mittel zum Verschieben des Kolbens (70) von einer ersten Position, in der die radiale Oberfläche des Kolbens in Kontakt ist mit dem Ende der Turbinenschaufeln, zu einer zweiten vom thermischen Schutzschild entfernten Position, in der die radiale Oberfläche so vom Ende der Turbinenschaufeln beabstandet ist, dass ein offener ringförmiger Kanal (94) zwischen dem Ende der Turbinenschaufeln und der radialen Oberfläche des Kolbens ensteht, so dass die Abgase vom Gas-Einlass (24) der Turbine durch den offenen ringförmigen Kanal (94) direkt auf das Turbinenrad (18) teilweise strömen können.
  2. Turbokompressor nach Anspruch 1, bei dem der Kolben (70a) einen U-förmigen Querschnitt mit dünner Wand hat, wodurch ein äußerer (94) und ein innerer Ring (96), die durch einen Steg verbunden sind, gebildet werden und dieser äußere Ring in einer zylindrischen Rille (100) des Turbinenkörpers (12) dicht aufgenommen ist und der innere Ring in engem Kontakt mit einer inneren peripheren Oberfläche der Austrittsöffnung für Abgase ist, wobei die inneren und äußeren Ringe als gestaffelte Dichtungen fungieren und der erwähnte Steg mit den Turbinenschaufeln (90) Kontakt hat, wenn der Kolben sich in der ersten Position befindet.
EP00985372A 2000-11-30 2000-11-30 Abgasturbolader mit variabler geometrie und einem ringschieber Expired - Lifetime EP1337739B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/FR2000/003350 WO2002044527A1 (fr) 2000-11-30 2000-11-30 Turbocompresseur a geometrie variable avec piston coulissant

Publications (2)

Publication Number Publication Date
EP1337739A1 EP1337739A1 (de) 2003-08-27
EP1337739B1 true EP1337739B1 (de) 2006-12-20

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EP00985372A Expired - Lifetime EP1337739B1 (de) 2000-11-30 2000-11-30 Abgasturbolader mit variabler geometrie und einem ringschieber

Country Status (11)

Country Link
US (1) US7024855B2 (de)
EP (1) EP1337739B1 (de)
JP (1) JP2004514840A (de)
KR (1) KR100737377B1 (de)
CN (1) CN100340742C (de)
AU (1) AU2001221812A1 (de)
CA (1) CA2423755C (de)
DE (1) DE60032523T2 (de)
HU (1) HU225776B1 (de)
MX (1) MXPA03004873A (de)
WO (1) WO2002044527A1 (de)

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US10138151B2 (en) 2013-05-22 2018-11-27 Johns Manville Submerged combustion burners and melters, and methods of use

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Also Published As

Publication number Publication date
DE60032523T2 (de) 2007-11-22
US7024855B2 (en) 2006-04-11
DE60032523D1 (de) 2007-02-01
CA2423755C (en) 2009-02-03
AU2001221812A1 (en) 2002-06-11
HUP0302896A2 (en) 2003-12-29
JP2004514840A (ja) 2004-05-20
CN1454285A (zh) 2003-11-05
CN100340742C (zh) 2007-10-03
HU225776B1 (en) 2007-08-28
US20040025504A1 (en) 2004-02-12
KR100737377B1 (ko) 2007-07-09
KR20030076979A (ko) 2003-09-29
EP1337739A1 (de) 2003-08-27
MXPA03004873A (es) 2005-02-14
CA2423755A1 (en) 2002-06-06
WO2002044527A1 (fr) 2002-06-06

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