EP0130408B1 - Einrichtung zur Verstellung des Turbinenzuströmquerschnittes eines Abgasturboladers - Google Patents

Einrichtung zur Verstellung des Turbinenzuströmquerschnittes eines Abgasturboladers Download PDF

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Publication number
EP0130408B1
EP0130408B1 EP84106486A EP84106486A EP0130408B1 EP 0130408 B1 EP0130408 B1 EP 0130408B1 EP 84106486 A EP84106486 A EP 84106486A EP 84106486 A EP84106486 A EP 84106486A EP 0130408 B1 EP0130408 B1 EP 0130408B1
Authority
EP
European Patent Office
Prior art keywords
turbine
lever
exhaust gas
adjustment element
annular link
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
Application number
EP84106486A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0130408A1 (de
Inventor
Jürg Weber
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 EP0130408A1 publication Critical patent/EP0130408A1/de
Application granted granted Critical
Publication of EP0130408B1 publication Critical patent/EP0130408B1/de
Expired 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
    • F01D17/141—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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00—Machine element or mechanism
    • Y10T74/18—Mechanical movements
    • Y10T74/18888—Reciprocating to or from oscillating
    • Y10T74/1892—Lever and slide
    • Y10T74/18944—Link connections

Definitions

  • the invention relates to a device in an exhaust gas turbocharger for adjusting the turbine inflow cross section according to the preamble of patent claim 1.
  • An adjustable ring slide enables a continuous change in the turbine inflow cross section.
  • the ring slide is adjusted here by axial displacement.
  • the ring slide is guided in a cylindrical bore in the gas housing, whereby there must be radial play between it and the housing.
  • the guide of the ring slide is provided with a labyrinth seal.
  • Running a relatively short cylindrical spool in a housing bore can cause difficulty in pinching the spool.
  • a further device of the type mentioned at the outset is known from US-A-4,214,850.
  • an axially displaceable ring is provided upstream of the radial turbine and is actuated via a system of pressure cylinder, drive rod, lever and shaft.
  • the object of the invention is to create a device for adjusting the turbine inflow cross-section, in which the adjusting member can be moved as smoothly and precisely as possible.
  • the advantages achieved by the invention are essentially to be seen in a quasi-translational guidance of the adjusting member which is favorable for a contact-free sealing, the low-friction joints of the ring-joint levers being arranged in the region of lower temperature. If the ring joint levers and the adjusting member are arranged in the pressure chamber of a pressure housing, the advantage is achieved that a single dynamically stressed sealing point against the environment lies on the passage of the drive shaft. This largely alleviates the problem of sealing.
  • the radial turbine shown in Fig. 1 is connected via a gas inlet opening 9 to an engine exhaust line, not shown.
  • the turbine shaft 1 is mounted in the turbine housing 4 and carries the turbine hub 2 provided with rotor blades 3.
  • the end face of the adjusting member 6 protruding into the turbine flow channel is rounded in conformity with the flow.
  • the completely open position of the adjusting member 6 corresponds to the maximum width E of the turbine inflow channel.
  • the maximum axial displacement S of the adjusting member 6 is determined by the width of the motor control range. It is essential here that the reduction in the turbine inflow cross section is coordinated in such a way that the absolute gas entry speed into the turbine remains approximately constant over the entire speed range.
  • the adjusting member 6 is suspended in two ring joint levers 7, .8 arranged concentrically to the turbine axis.
  • the lever arm R 1 of the first ring joint lever 7, which is closer to the turbine, is longer than that R 2 of the second ring joint lever 8.
  • the lengths of the lever arms R 1 and R 2 , their mutual axial distance C and the distance D of the first ring joint lever 7 from the position of the adjusting member 6 to be sealed are coordinated such that a minimal deviation of the path of the adjusting member 6 from its translational straight guidance is achieved .
  • a pressure housing 5, which has a gas outlet opening 10, is connected to the turbine housing 4.
  • the rotationally symmetrical inner part 5 'of the pressure housing 5 is designed as a hollow, coaxially arranged cylinder. Its end facing the turbine is profiled in a flow-conforming manner and determines the width E of the turbine inflow channel.
  • the pressure housing 5 encloses a pressure chamber 5 ".
  • the ring joint levers 7, 8 and the adjusting member 6 are arranged in the pressure chamber 5 "of the pressure housing 5, where they are in the region of lower temperatures.
  • This arrangement of the ring joint levers 7, 8 and the adjusting member 6 in the pressure chamber 5 "of the pressure housing 5 has the advantage that the bushings to be sealed between the turbine flow channel under the gas pressure and the atmosphere are kept to a minimum. Only the bearing of the joint bolt 14 must be sealed This role was performed by a simple shaft seal 16.
  • the lever arm R 2 of the articulated lever 8 can preferably be determined as a function of other influencing variables as follows:
  • the adjusting member 6 moves with its cylindrical, inwardly open surface along the outer cylindrical surface of the inner part 5 'of the pressure housing 5 without contact.
  • the adjusting member 6, with its cylindrical, outwardly open surface, also moves without contact along the cylindrical surface of the axial bore arranged in the turbine housing 4.
  • the radial gap between the inner part 5 'of the pressure housing 5 and the adjusting element 6 and the radial gap between the turbine housing 4 and the adjusting element 6 must be as small as possible, since otherwise due to the pressure gradients present in the circumferential direction of the turbine inflow channel and the pressure difference across the adjusting element. 6 Flow losses and an intensive swirling of the engine exhaust gas in the pressure chamber 5 "would arise. The swirling of the hot engine exhaust gas in the pressure chamber 5" could have negative effects on the effect of the joints of the trapezoidal quadrilateral joint.
  • the longer annular joint lever 7 is shown on the cross section shown in FIG. 2.
  • This ring joint lever 7 is mounted below in the pressure housing 5 by means of a joint pin 12.
  • the adjusting member 6 is rotatably suspended by means of a joint pin 11.
  • FIG. 3 shows a cross section along line B-B in FIG. 1.
  • the second ring joint lever 8 is in turn mounted in the pressure housing 5 by means of a two-part hinge pin 14 on which a drive lever 15 is fixedly arranged.
  • the hinge pin 14 has a shaft seal 16 in its bearing facing the drive lever 15.
  • the adjusting member 6 is rotatably suspended on the top of the ring lever 8 by means of a hinge pin 13.
  • the mode of operation of the device can be seen from the following: When the engine is fully loaded, the adjusting member 6 is in the open position, as shown in FIG. 1. If the engine load is reduced, the exhaust gas pressure in front of the turbine drops. The adjusting member 6 is now automatically or manually in the Flow channel shifted in, the distance E between the adjusting member 6 and the housing 4 and thus the turbine inflow cross section decreases.
  • the engine exhaust gas pressure can, for example, be used as the control variable in the case of automatic control of the adjusting member 6.
  • the displacement of the adjusting member 6 is shown in dashed lines at the minimum load of the engine in FIG. 1 and is denoted by S.
  • the mechanism for actuating the adjusting member 6 is a trapezoidal three-dimensional articulated quadrilateral whose pivot points are formed by two articulated bolts 12, 14 arranged in the housing 5, and by bolts 11, 13 arranged in each of the two articulated levers 7, 8.
  • the ring joint lever 8 By pivoting the drive lever 15 which is fixedly connected to the bolt 14 and this in turn to the ring joint 8, the ring joint lever 8 now swivels the bolt 14 by the same pivoting angle as the drive lever 15.
  • the bolt 13 moves along an arc-like path with a radius R 2 around the hinge pin 14. This movement is transmitted to the adjusting member 6, the adjusting member 6 being pushed in an approximately axial direction.
  • the ring joint lever 7 Since the adjusting member 6 is articulated by means of the bolt 11 in the ring joint lever 7, the ring joint lever 7 also pivots in the same direction as the ring joint lever 8, but at a somewhat smaller angle, whereby the joint bolt 11 moves on an arc-like path with a radius R. the hinge pin 12 moves. Since the radius R 2 is smaller than R, with a pivoting movement of the two ring joint levers 7, 8 in the direction of the turbine rotor 2, 3, the end face of the adjusting element 6 facing the turbine is lifted up out of its descending circular path, so that the movement of the Adjustment element 6 deviates only slightly from a pure translation. The displacement of the adjusting element can therefore be regarded as quasi-linear.
  • the radial turbine according to FIG. 4 differs from that according to FIG. 1 in that the adjusting element 6 is designed in the form of a displaceable boundary wall of the spiral flow channel arranged in the turbine housing 4.
  • the shape of the adjusting member 6 that matches the spiral flow channel is shown in FIG. 5 with a dash-dot line.
  • the adjustment mechanism is here completely identical to that in FIG. 1.
  • the advantage of the invention is seen in particular in the fact that a precise and low-friction, quasi-translational guidance of the adjusting element 6 is created with a contact-free seal, in which the signs of wear and operating malfunctions are largely eliminated and the service life of the device is positively influenced.
  • the invention also encompasses other types of turbines, which are provided, for example, with a turbine guide apparatus which is partially radially flowed through and with an adjusting element which can be displaced in the axial direction.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
EP84106486A 1983-06-29 1984-06-06 Einrichtung zur Verstellung des Turbinenzuströmquerschnittes eines Abgasturboladers Expired EP0130408B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH356083 1983-06-29
CH3560/83 1983-06-29

Publications (2)

Publication Number Publication Date
EP0130408A1 EP0130408A1 (de) 1985-01-09
EP0130408B1 true EP0130408B1 (de) 1987-09-30

Family

ID=4258626

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84106486A Expired EP0130408B1 (de) 1983-06-29 1984-06-06 Einrichtung zur Verstellung des Turbinenzuströmquerschnittes eines Abgasturboladers

Country Status (5)

Country Link
US (1) US4571154A (da)
EP (1) EP0130408B1 (da)
JP (1) JPS6013925A (da)
DE (1) DE3466572D1 (da)
DK (1) DK155843C (da)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006060126A1 (de) * 2006-12-20 2008-06-26 Mahle International Gmbh Ladeeinrichtung

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3734386A1 (de) * 1987-10-10 1989-04-20 Daimler Benz Ag Abgasturbolader fuer eine brennkraftmaschine
US5057430A (en) * 1988-09-15 1991-10-15 Biotronic Systems Corporation Biochemical sensor responsive to bubbles
GB2326198A (en) * 1997-06-10 1998-12-16 Holset Engineering Co Variable geometry turbine
DE10310678B3 (de) * 2003-03-12 2004-09-23 Atlas Copco Energas Gmbh Expansionsturbinenstufe
US8109090B2 (en) * 2006-10-27 2012-02-07 Komatsu Ltd. Variable turbo supercharger and method of returning oil from hydraulic drive
GB0811228D0 (en) * 2008-06-19 2008-07-30 Cummins Turbo Tech Ltd Variable geometric turbine
US20110173973A1 (en) * 2010-01-20 2011-07-21 International Engine Intellectrual Property Company, LLC Turbine inlet flow modulator
GB2483995B (en) * 2010-09-22 2016-12-07 Cummins Ltd Variable geometry turbine
CN102536438A (zh) * 2012-01-18 2012-07-04 无锡威孚英特迈增压技术有限公司 涡轮壳滑动变截面装置

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US565848A (en) * 1896-08-11 Turbine
DE903052C (de) * 1941-12-28 1954-02-01 Maschf Augsburg Nuernberg Ag Abgasturbogeblaese fuer Brennkraftmaschinen, insbesondere Zweitakttbrennkraftmaschinen
CH277111A (de) * 1948-02-20 1951-08-15 Ag Scintilla Verfahren zum Regulieren von Radialturbinen und Einrichtung zur Durchführung desselben.
US2861774A (en) * 1950-02-16 1958-11-25 Alfred J Buchi Inlet control for radial flow turbines
GB881407A (en) * 1957-02-13 1961-11-01 Technica Ets Improvements in or relating to hydraulic impulse turbines
CH557960A (de) * 1972-11-08 1975-01-15 Bbc Sulzer Turbomaschinen Vorrichtung fuer die leitschaufelverstellung.
US3975911A (en) * 1974-12-27 1976-08-24 Jury Borisovich Morgulis Turbocharger
DE2633587C2 (de) * 1976-07-27 1985-05-23 Klöckner-Humboldt-Deutz AG, 5000 Köln Abgasturbolader für eine Brennkraftmaschine
US4214850A (en) * 1977-10-12 1980-07-29 Ishikawajima-Harima Jukogyo Kabushiki Kaisha Variable-capacity radial turbine
JPS6052293B2 (ja) * 1978-04-11 1985-11-18 石川島播磨重工業株式会社 可変容量ラジアルタ−ビン
US4499731A (en) * 1981-12-09 1985-02-19 Bbc Brown, Boveri & Company, Limited Controllable exhaust gas turbocharger

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006060126A1 (de) * 2006-12-20 2008-06-26 Mahle International Gmbh Ladeeinrichtung

Also Published As

Publication number Publication date
DK155843B (da) 1989-05-22
US4571154A (en) 1986-02-18
DE3466572D1 (en) 1987-11-05
EP0130408A1 (de) 1985-01-09
DK155843C (da) 1989-10-02
JPS6013925A (ja) 1985-01-24
DK314784D0 (da) 1984-06-27
DK314784A (da) 1984-12-30
JPH0475370B2 (da) 1992-11-30

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