EP0143182A1 - Turbo-soufflante à deux étages comportant un dispositif pour éviter la perte du lubrifiant - Google Patents

Turbo-soufflante à deux étages comportant un dispositif pour éviter la perte du lubrifiant Download PDF

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Publication number
EP0143182A1
EP0143182A1 EP84109544A EP84109544A EP0143182A1 EP 0143182 A1 EP0143182 A1 EP 0143182A1 EP 84109544 A EP84109544 A EP 84109544A EP 84109544 A EP84109544 A EP 84109544A EP 0143182 A1 EP0143182 A1 EP 0143182A1
Authority
EP
European Patent Office
Prior art keywords
exhaust gas
pressure
line
lubricating oil
bearing housing
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.)
Ceased
Application number
EP84109544A
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German (de)
English (en)
Inventor
Hansulrich Dr. Hörler
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0143182A1 publication Critical patent/EP0143182A1/fr
Ceased legal-status Critical Current

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Classifications

    • 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
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F02B39/14—Lubrication of pumps; Safety measures therefor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • 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
    • F02B1/00—Engines characterised by fuel-air mixture compression
    • F02B1/02—Engines characterised by fuel-air mixture compression with positive ignition
    • F02B1/04—Engines characterised by fuel-air mixture compression with positive ignition with fuel-air mixture admission into cylinder

Definitions

  • the present invention relates to an exhaust gas turbocharger for two-stage supercharging of an internal combustion engine with a device for avoiding lubricant losses according to the preamble of patent claim 1.
  • the bearing of the high-pressure stage shaft is often arranged in a bearing housing between the turbine wheel and the compressor wheel, this housing serving as a collecting container for the oil escaping from the bearings, from which it enters the engine oil sump or into an oil tank separated from this flows back or is pumped there. Since it is not possible to seal the above-mentioned housing against the compressor housing and the turbine housing in such a way that oil does not enter them, the pressure in the bearing housing must always be lower than the pressures in the compressor or turbine housing. The pressure difference However, it must not be so large that the efficiency of the compressor and turbine are reduced. The pressure in the bearing housing should therefore only be as close as possible to the lower of the pressures in the compressor or turbine housing.
  • unsupported sealing rings can be used, which have a better sealing effect than supported sealing rings and are also cheaper.
  • sealing air is often branched off from the charge air line to cool the turbine-side shaft stub and to prevent the entry of exhaust gases into the bearing housing and into the compressor.
  • the labyrinth seal between the compressor housing and the compressor wheel is designed with a radius such that it is on the compressor wheel and essentially cancel the axial thrust acting on the turbine wheel.
  • the air behind the labyrinth is also discharged into the environment.
  • turbochargers strive to be able to use such turbocharger types, originally designed as single-stage turbochargers, with as few modifications as possible as the high-pressure stage of two-stage turbochargers.
  • the most important changes and adaptations to the higher pressures upstream of the compressor and behind the turbine are measures that increase the pressure in the sealing air ducts and in the bearing housing to such an extent that the small pressure difference mentioned at the outset is achieved.
  • this device is intended for gasoline engines that have a throttle valve in the intake line upstream of the compressor.
  • Single or two-stage turbochargers of diesel engines do not have a throttle valve in the intake line and are therefore not suitable for the system described.
  • the object of the invention is to be solved, since the prevention of lubricant losses in single-stage exhaust gas turbochargers of diesel engines is not a problem because of the pressure ratios mentioned in the introduction in the compressor, turbine and bearing housing two-stage supercharged diesel engines, where this problem arises in the high pressure stage.
  • the one-stage turbocharger shown in FIG. 1 has a compressor 1 which sucks atmospheric air through an intake line 2, compresses it and conveys it through a charge air line 3 into the working cylinders of a diesel engine, not shown.
  • the compressor 1 is driven by an exhaust gas turbine 4 which is acted upon by the exhaust gases coming from the engine via an exhaust gas line 5.
  • the exhaust gas relaxing in the turbine 4 exits through an exhaust pipe 6.
  • Compressor 1 and turbine 5 sit on a common shaft 7, which is mounted in a bearing housing 8 in bearings 9 and 10.
  • the lubricating oil is supplied to the bearings 9 and 10 from a lubricating oil tank 11, from which a lubricating oil pump 12 presses the oil into the bearings 9 and 10 via an oil suction line 13 and an oil pressure line 14 through an oil filter 15, an oil cooler 16 and a lubricating oil supply line 17 .
  • the oil dripping from the bearings collects in the bearing housing 8, from which it flows back into the lubricating oil tank 11 through an oil return line 18.
  • This lubricating oil circuit applies to larger engines with their own lubricating oil tank outside the engine crankcase.
  • the engine lubricating oil in the crankcase is usually used to lubricate the exhaust gas turbocharger.
  • the pump 12 conveys one of the Oil supply line 17 branching, dashed oil line 19 draws part of the oil to the lubrication points of the engine, from which, as symbolized by an oil return line 20, it flows back into the crankcase of the engine symbolized by the oil tank 11.
  • the modification in box 23 compared to the training in box 22 is that the vent pipe 21 is conductively connected to the low-pressure charge air line 26 by a compensating line 25, the latter being materially identical to the intake line 2, but now between the low-pressure charger (not shown) and the one above shown high-pressure charger receives the pre-compressed charge air.
  • a compensating line 25 the latter being materially identical to the intake line 2, but now between the low-pressure charger (not shown) and the one above shown high-pressure charger receives the pre-compressed charge air.
  • the pressure difference between the bearing housing 8 and the compressor 1, which now provides the high-pressure charging is so small that the aforementioned Invention task, prevention of lubricant loss and the lowest possible air loss from the high pressure compressor is fulfilled.
  • the pressure difference that the oil pump 12 has to be overcome is the same as when using the charger for single-stage charging.
  • Box 24 shows a device in the event that the supercharger lubricating oil circuit is branched from that of the engine, and it is not desirable that the associated oil tank or crankcase be pressurized.
  • This device shown larger in FIG. 4, sits on the bottom of a specially provided air separator vessel and consists of a level control float 27 in conjunction with an oil drain pipe 28, the upper end of which is closed by an end plate 29 and two slots 30 extending over a large part of the circumference having.
  • the float 27 consists of a float vessel 31 and a bell 32 fastened to the underside thereof with slots 33 in the manner of the above-mentioned slots 30 in the oil drain pipe 28. The mode of operation can be seen from FIG. 4.
  • the lower edge of the bell 32 frees the slots 30 in the drain pipe 28 and oil flows into the crankcase of the engine until the lubricating oil level has dropped again to the lowest level.
  • the oil content separates the crankcase, in which there is essentially ambient pressure, from the space above the lubricating oil level, which is connected to the low-pressure charge air line 26 by a compensating line 28 and in which, like in the bearing housing 8, the pressure prevails after the first charging stage.
  • a vent pipe 35 is provided for venting the crankcase.
  • the high-pressure exhaust gas turbocharger for two-stage supercharging shown in FIG. 5 can be obtained by modifications according to the invention from a low-pressure exhaust gas supercharger with sealing air channels for one-stage supercharging.
  • the broken line VI shown in FIG. 6 shows the design of the charger for single-stage charging before the modification.
  • the sealing air symbolized by the small white arrows 36 flows from the high-pressure charge air line 37 into a sealing air channel 38 which is connected to a sealing air ring channel 40 surrounding the bearing housing 39.
  • This sealing air ring duct 40 is delimited by an inner casing forming the bearing housing 39 and an outer housing 41.
  • Transverse walls 42 and 43 delimit chambers separated from this sealing air ring channel 40, which are located between these transverse walls 42, 43 and the compressor 44 or the exhaust gas turbine 45, but these chambers are in conductive communication with the sealing air ring channel.
  • the sealing air ring channel When used for single-stage charging, the sealing air ring channel, as can be seen in FIG. 6, is in conductive connection with the surroundings via ventilation ports 46 and 47, which are covered by caps 48 and 49.
  • these ventilation connections 46 and 47 are conductively connected to the low-pressure charge air duct 53 by lines 50 and 51, which open into a common equalization line 52, as a result of which such a pressure difference between the compressor 44 in the sense of the task of the invention and the interior of the bearing housing 39 sets that lubricant is prevented from escaping from the bearing housing into the compressor and / or the turbine housing.
  • the interior of the lubricating oil tank 54 can also be connected to the low-pressure charge air line 53 by a compensating line 55, which also solves the problem of tank ventilation.
  • the tanks By venting the lubricating oil tanks 11 and 54 into the low-pressure charge air line 26 and 55 in question instead of the environment, the tanks are under the same pressure as the low-pressure charge air lines, so that the pressure difference to be overcome by the oil pump is the same as when using the exhaust gas turbocharger for one single-stage charging.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
EP84109544A 1983-09-01 1984-08-10 Turbo-soufflante à deux étages comportant un dispositif pour éviter la perte du lubrifiant Ceased EP0143182A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH479683 1983-09-01
CH4796/83 1983-09-01

Publications (1)

Publication Number Publication Date
EP0143182A1 true EP0143182A1 (fr) 1985-06-05

Family

ID=4282695

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84109544A Ceased EP0143182A1 (fr) 1983-09-01 1984-08-10 Turbo-soufflante à deux étages comportant un dispositif pour éviter la perte du lubrifiant

Country Status (6)

Country Link
US (1) US4752193A (fr)
EP (1) EP0143182A1 (fr)
JP (1) JPS60156935A (fr)
KR (1) KR890000570B1 (fr)
IN (1) IN161658B (fr)
PL (1) PL249402A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19627412C1 (de) * 1996-07-08 1998-01-29 Daimler Benz Ag Vorrichtung zur Entlüftung einer Brennkraftmaschine
DE102005033660A1 (de) * 2005-07-19 2007-01-25 GM Global Technology Operations, Inc., Detroit Führungsrohr für einen Ölmessstab eines Verbrennungsmotors
DE102007030277A1 (de) * 2007-06-28 2009-01-08 Mann + Hummel Gmbh Turbolader für eine Brennkraftmaschine
DE102008034343B4 (de) * 2008-07-23 2017-03-16 Continental Mechanical Components Germany Gmbh Turbolader mit abgedichteter und gekühlter Lagerung
DE102018130772A1 (de) * 2018-12-04 2020-06-04 Man Energy Solutions Se Turbolader, Verfahren zur Herstellung einer Baugruppe eines Turboladers und Verwendung
EP3845741A1 (fr) * 2019-12-30 2021-07-07 Hamilton Sundstrand Corporation Soupape de purge d'air de réservoir d'huile pour un moteur d'aéronef

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4926641A (en) * 1989-01-11 1990-05-22 Keller Robert A Turbocharger lubrication system
US5026260A (en) * 1989-09-08 1991-06-25 Allied-Signal Inc. Turbocharger with turbine backplate and center housing oil shield
US5161960A (en) * 1991-11-12 1992-11-10 Allied-Signal Inc. Turbocharger with liquid cooled housing
DE19620901C1 (de) * 1996-05-23 1997-08-21 Grundfos As Tauchmotor zum Antrieb einer Kreiselpumpe
US6192871B1 (en) 1998-10-30 2001-02-27 Vortech Engineering, Inc. Compact supercharger
US7299792B1 (en) 2000-09-22 2007-11-27 Accessible Technologies, Inc. Centrifugal compressor with improved lubrication system for gear-type transmission
DE10121920C2 (de) * 2001-05-05 2003-05-15 Man B & W Diesel Ag Lagergehäuse eines Abgasturboladers für eine Brennkraftmaschine
JP2003035154A (ja) * 2001-07-19 2003-02-07 Honda Motor Co Ltd 過給機付きエンジンを搭載した小型滑走艇
JP3958054B2 (ja) * 2002-01-31 2007-08-15 株式会社東芝 回転機械の軸受油循環系統の改修方法
WO2004063535A1 (fr) * 2003-01-10 2004-07-29 Honeywell International Inc. Turbocompresseur et systeme de suralimentation a plusieurs turbocompresseurs
US6745568B1 (en) * 2003-03-27 2004-06-08 Richard K. Squires Turbo system and method of installing
US7128061B2 (en) * 2003-10-31 2006-10-31 Vortech Engineering, Inc. Supercharger
US7476090B2 (en) * 2005-10-11 2009-01-13 International Engine Intellectual Property Company, Llc Vented turbocharger center housing and method
US20070092387A1 (en) * 2005-10-21 2007-04-26 Borgwarner Inc. Oil discharge assembly for a turbocharger
GB0611044D0 (en) * 2006-06-05 2006-07-12 Wabco Automotive Uk Ltd Multiple inlet pump
JP4720783B2 (ja) * 2007-05-09 2011-07-13 日産自動車株式会社 過給器の潤滑装置
US20100175377A1 (en) * 2009-01-12 2010-07-15 Will Hippen Cooling an electrically controlled turbocharger
US7946118B2 (en) * 2009-04-02 2011-05-24 EcoMotors International Cooling an electrically controlled turbocharger
CN102265011B (zh) * 2009-04-24 2013-10-02 三菱重工业株式会社 混合排气涡轮增压器
DE102011002562B4 (de) * 2011-01-12 2020-02-06 Ford Global Technologies, Llc Aufgeladene flüssigkeitsgekühlte Brennkraftmaschine
US8915708B2 (en) * 2011-06-24 2014-12-23 Caterpillar Inc. Turbocharger with air buffer seal
US8959911B2 (en) * 2011-10-06 2015-02-24 GM Global Technology Operations LLC Engine assembly including fluid control to boost mechanism
DE102012206650B4 (de) * 2012-04-23 2024-03-28 Ford Global Technologies, Llc Turboladeranordnung für einen Verbrennungsmotor
RU2680278C2 (ru) * 2014-10-02 2019-02-19 Мту Фридрихсхафен Гмбх Система охлаждения и двигатель внутреннего сгорания с такой системой охлаждения
CN104847480B (zh) * 2015-05-22 2017-06-20 上海齐耀发动机有限公司 二级增压的废气涡轮增压器
US10036325B2 (en) * 2016-03-30 2018-07-31 General Electric Company Variable flow compressor of a gas turbine
EP3508708B1 (fr) * 2017-10-26 2020-12-02 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbocompresseur
JP2022068783A (ja) * 2020-10-22 2022-05-10 三菱重工マリンマシナリ株式会社 過給機
CN112627985A (zh) * 2020-12-02 2021-04-09 北京动力机械研究所 一种燃气涡轮发动机润滑系统的压力平衡机构

Citations (9)

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CH266730A (de) * 1948-08-11 1950-02-15 Siegfried Keller & Co Vorrichtung zur Vermeidung von Schmiermittelverlusten bei hochtourigen Turbomaschinen mit fliegender Läuferanordnung.
CH266729A (de) * 1948-08-11 1950-02-15 Siegfried Keller & Co Vorrichtung zur Vermeidung von Schmiermittelverlusten bei hochtourigen Turbomaschinen mit fliegender Läuferanordnung.
GB664600A (en) * 1949-02-04 1952-01-09 English Electric Co Ltd Improvements in and relating to gas turbines
FR1203602A (fr) * 1957-06-20 1960-01-20 United Aircraft Corp Ensemble compresseur-turbine
GB911449A (en) * 1960-01-12 1962-11-28 Gen Electric Co Ltd Improvements in or relating to shaft bearing
GB966352A (en) * 1962-02-13 1964-08-12 Ludwig Bolkow System for sealing and lubricating heavy duty shaft bearings
DE2209909A1 (de) * 1972-03-02 1973-10-25 Porsche Ag Vorrichtung zur vermeidung von schmiermittelverlusten bei abgasturboladern
GB2011558A (en) * 1977-12-27 1979-07-11 Cummins Engine Co Inc Turbocharger assembly
DE8026375U1 (de) * 1981-01-15 Dr.Ing.H.C. F. Porsche Ag, 7000 Stuttgart Vorrichtung zur Vermeidung von Schmiermittelverlusten bei einem Abgasturbolader für Brennkraftmaschinen

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DE812950C (de) * 1948-08-11 1951-09-06 Eberspaecher J Sicherung des Schmiermittelraumes bei hochtourigen Stroemungsmaschinen durch Entlueftung
US2604188A (en) * 1949-08-19 1952-07-22 A V Roe Canada Ltd Oil supply and scavenge system
US2646212A (en) * 1950-11-30 1953-07-21 Edward P Kellie Oil level equalizing device for multiple compressor arrangement
GB1062983A (en) * 1962-12-21 1967-03-22 Perkins Engines Ltd Pressure charging system for internal combustion engines
US4009972A (en) * 1975-07-10 1977-03-01 Wallace-Murray Corporation Turbocharger lubrication and exhaust system

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE8026375U1 (de) * 1981-01-15 Dr.Ing.H.C. F. Porsche Ag, 7000 Stuttgart Vorrichtung zur Vermeidung von Schmiermittelverlusten bei einem Abgasturbolader für Brennkraftmaschinen
CH266730A (de) * 1948-08-11 1950-02-15 Siegfried Keller & Co Vorrichtung zur Vermeidung von Schmiermittelverlusten bei hochtourigen Turbomaschinen mit fliegender Läuferanordnung.
CH266729A (de) * 1948-08-11 1950-02-15 Siegfried Keller & Co Vorrichtung zur Vermeidung von Schmiermittelverlusten bei hochtourigen Turbomaschinen mit fliegender Läuferanordnung.
GB664600A (en) * 1949-02-04 1952-01-09 English Electric Co Ltd Improvements in and relating to gas turbines
FR1203602A (fr) * 1957-06-20 1960-01-20 United Aircraft Corp Ensemble compresseur-turbine
GB911449A (en) * 1960-01-12 1962-11-28 Gen Electric Co Ltd Improvements in or relating to shaft bearing
GB966352A (en) * 1962-02-13 1964-08-12 Ludwig Bolkow System for sealing and lubricating heavy duty shaft bearings
DE2209909A1 (de) * 1972-03-02 1973-10-25 Porsche Ag Vorrichtung zur vermeidung von schmiermittelverlusten bei abgasturboladern
GB2011558A (en) * 1977-12-27 1979-07-11 Cummins Engine Co Inc Turbocharger assembly

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19627412C1 (de) * 1996-07-08 1998-01-29 Daimler Benz Ag Vorrichtung zur Entlüftung einer Brennkraftmaschine
DE102005033660A1 (de) * 2005-07-19 2007-01-25 GM Global Technology Operations, Inc., Detroit Führungsrohr für einen Ölmessstab eines Verbrennungsmotors
DE102007030277A1 (de) * 2007-06-28 2009-01-08 Mann + Hummel Gmbh Turbolader für eine Brennkraftmaschine
DE102008034343B4 (de) * 2008-07-23 2017-03-16 Continental Mechanical Components Germany Gmbh Turbolader mit abgedichteter und gekühlter Lagerung
DE102018130772A1 (de) * 2018-12-04 2020-06-04 Man Energy Solutions Se Turbolader, Verfahren zur Herstellung einer Baugruppe eines Turboladers und Verwendung
EP3845741A1 (fr) * 2019-12-30 2021-07-07 Hamilton Sundstrand Corporation Soupape de purge d'air de réservoir d'huile pour un moteur d'aéronef
US11383854B2 (en) 2019-12-30 2022-07-12 Hamilton Sundstrand Corporation Oil reservoir vent valve

Also Published As

Publication number Publication date
IN161658B (fr) 1988-01-09
KR890000570B1 (ko) 1989-03-21
KR850003182A (ko) 1985-06-13
PL249402A1 (en) 1985-05-21
JPS60156935A (ja) 1985-08-17
US4752193A (en) 1988-06-21

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