EP1337739B1 - Turbocompresseur a geometrie variable avec piston coulissant - Google Patents

Turbocompresseur a geometrie variable avec piston coulissant 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
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1337739A1 (fr
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
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 Honeywell Garrett SA filed Critical Honeywell Garrett SA
Publication of EP1337739A1 publication Critical patent/EP1337739A1/fr
Application granted granted Critical
Publication of EP1337739B1 publication Critical patent/EP1337739B1/fr
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)
EP00985372A 2000-11-30 2000-11-30 Turbocompresseur a geometrie variable avec piston coulissant Expired - Lifetime EP1337739B1 (fr)

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 (fr) 2003-08-27
EP1337739B1 true EP1337739B1 (fr) 2006-12-20

Family

ID=8848140

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00985372A Expired - Lifetime EP1337739B1 (fr) 2000-11-30 2000-11-30 Turbocompresseur a geometrie variable avec piston coulissant

Country Status (11)

Country Link
US (1) US7024855B2 (cg-RX-API-DMAC7.html)
EP (1) EP1337739B1 (cg-RX-API-DMAC7.html)
JP (1) JP2004514840A (cg-RX-API-DMAC7.html)
KR (1) KR100737377B1 (cg-RX-API-DMAC7.html)
CN (1) CN100340742C (cg-RX-API-DMAC7.html)
AU (1) AU2001221812A1 (cg-RX-API-DMAC7.html)
CA (1) CA2423755C (cg-RX-API-DMAC7.html)
DE (1) DE60032523T2 (cg-RX-API-DMAC7.html)
HU (1) HU225776B1 (cg-RX-API-DMAC7.html)
MX (1) MXPA03004873A (cg-RX-API-DMAC7.html)
WO (1) WO2002044527A1 (cg-RX-API-DMAC7.html)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10138151B2 (en) 2013-05-22 2018-11-27 Johns Manville Submerged combustion burners and melters, and methods of use

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WO2004015276A1 (en) * 2002-08-13 2004-02-19 Honeywell International, Inc. Compressor
EP1925784B1 (en) * 2002-09-05 2011-07-20 Honeywell International Inc. Turbocharger comprising a variable nozzle device
EP1543220B1 (en) * 2002-09-05 2008-05-21 Honeywell International Inc. Turbocharger comprising a variable nozzle device
JP2005539177A (ja) 2002-09-18 2005-12-22 ハネウェル・インターナショナル・インコーポレーテッド ターボチャージャのための可変ノズル装置及び同装置の作動方法
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WO2004074643A1 (en) * 2003-02-19 2004-09-02 Honeywell International Inc. Nozzle device for a turbocharger and associated control method
EP1595059B1 (en) * 2003-02-19 2018-04-25 Honeywell International Inc. Turbine having a variable throat
EP1700005B1 (en) * 2003-12-10 2014-12-03 Honeywell International Inc. Variable nozzle device for a turbocharger
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US7407364B2 (en) * 2005-03-01 2008-08-05 Honeywell International, Inc. Turbocharger compressor having ported second-stage shroud, and associated method
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US8191367B2 (en) * 2005-11-16 2012-06-05 Honeywell International Inc. Sliding piston cartridge and turbocharger incorporating same
EP1816317B1 (en) * 2006-02-02 2013-06-12 IHI Corporation Turbocharger with variable nozzle
GB0615495D0 (en) 2006-08-04 2006-09-13 Cummins Turbo Tech Ltd Variable geometry turbine
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US20080271449A1 (en) * 2007-05-01 2008-11-06 Quentin Roberts Turbocharger with sliding piston, having overlapping fixed and moving vanes
US7762067B2 (en) * 2007-08-21 2010-07-27 Honeywell International, Inc. Turbocharger with sliding piston assembly
GB0801846D0 (en) * 2008-02-01 2008-03-05 Cummins Turbo Tech Ltd A variable geometry turbine with wastegate
DE102008009604A1 (de) * 2008-02-15 2009-08-20 Rolls-Royce Deutschland Ltd & Co Kg Gehäusestrukturierung zum Stabilisieren der Strömung in einer Strömungsarbeitsmaschine
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GB2461720B (en) * 2008-07-10 2012-09-05 Cummins Turbo Tech Ltd A variable geometry turbine
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JP2013535615A (ja) * 2010-08-05 2013-09-12 ボーグワーナー インコーポレーテッド 排気ガスターボチャージャ
GB2483995B (en) 2010-09-22 2016-12-07 Cummins Ltd Variable geometry turbine
CN102297016B (zh) 2011-08-15 2012-12-12 无锡凯迪增压器配件有限公司 双叶片喷嘴系统的涡轮增压器
KR101917223B1 (ko) * 2012-04-24 2019-01-29 보르그워너 인코퍼레이티드 Vtg 터보차저를 위한 베인 팩 조립체
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CN109098780B (zh) * 2018-05-24 2024-05-14 中车大连机车研究所有限公司 一种涡轮增压器燃气废气进排气壳体
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10138151B2 (en) 2013-05-22 2018-11-27 Johns Manville Submerged combustion burners and melters, and methods of use

Also Published As

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

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