EP0678657B1 - Turbolader - Google Patents

Turbolader Download PDF

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Publication number
EP0678657B1
EP0678657B1 EP95107138A EP95107138A EP0678657B1 EP 0678657 B1 EP0678657 B1 EP 0678657B1 EP 95107138 A EP95107138 A EP 95107138A EP 95107138 A EP95107138 A EP 95107138A EP 0678657 B1 EP0678657 B1 EP 0678657B1
Authority
EP
European Patent Office
Prior art keywords
piston
turbine
turbocharger apparatus
housing
chamber
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
EP95107138A
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English (en)
French (fr)
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EP0678657A3 (de
EP0678657A2 (de
Inventor
Malcolm George Leavesley
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.)
Individual
Original Assignee
Individual
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
Priority claimed from GB888812664A external-priority patent/GB8812664D0/en
Priority claimed from GB888817230A external-priority patent/GB8817230D0/en
Priority claimed from GB888827153A external-priority patent/GB8827153D0/en
Priority claimed from GB888827761A external-priority patent/GB8827761D0/en
Priority claimed from GB898901803A external-priority patent/GB8901803D0/en
Application filed by Individual filed Critical Individual
Publication of EP0678657A2 publication Critical patent/EP0678657A2/de
Publication of EP0678657A3 publication Critical patent/EP0678657A3/xx
Application granted granted Critical
Publication of EP0678657B1 publication Critical patent/EP0678657B1/de
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
    • F01D17/141—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
    • 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
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • 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

  • This invention relates to turbocharger apparatus and it relates more especially to variable turbocharger apparatus.
  • turbocharger apparatus Different types are known, see for example DE-A-3 244 190 and US-A-4 403 914.
  • One known type of turbocharger apparatus comprises a housing, a compressor mounted for rotation in the housing, a turbine mounted for rotation in the housing, a first inlet for enabling air to be conducted to the compressor, an outlet for air from the compressor, a second inlet for enabling exhaust gases from an engine to be conducted to the turbine, and a chamber which surrounds the turbine and which receives the exhaust gases from the second inlet before the exhaust gases are conducted to the turbine.
  • This known type of turbocharger apparatus is such that there is a fixed gap through which the exhaust gases in the chamber can pass to the turbine.
  • this gap is chosen to be a compromise between the various different sizes of gap that are ideally required for different engine operating conditions. This means that, for most engine operating conditions, the gap is not exactly correct and the turbocharger apparatus thus operates at less than its optimum performance. For example, with a relatively small gap, the turbocharger apparatus gives a quick response but excessive pressure tends to build up in the chamber. With a large gap, the build up of excessive pressure in the chamber is avoided but then the response time of the turbine apparatus is slow.
  • GB-A-2218744 discloses a turbocharger in which the guide vanes are removed from the gas flow. This decreases the efficiency of operation of the turbocharger. Also, in GB-A-2218744 hot gases are allowed to bypass to the low pressure side of the turbine apparatus, thereby preventing all of the gases from working on the turbine. Also, the gases that are lost to the low pressure side of the turbocharger apparatus contact the bearing assembly and may eventually cause bearing assembly failure.
  • variable turbocharger apparatus comprising a compressor housing, a compressor mounted for rotation in the compressor housing, a turbine housing, a turbine mounted for roatation in the turbine housing, a first inlet for enabling air to be conducted to the compressor, an outlet for air from the compressor, a second inlet for enabling exhaust gases from an engine to be conducted to the turbine, a chamber which surrounds the turbine and which receives the exhaust gases from the second inlet before the exhaust gases are conducted to the turbine, a piston which is positioned between the turbine and the turbine housing and which is slidable backwards and forwards to form a movable wall separating the turbine from the chamber which surrounds the turbine, a bearing assembly for allowing the rotation of the compressor and the turbine, and a heat shield for shielding the bearing assembly from the exhaust gases, the piston having a plurality of vanes, the piston being such that in its closed position it terminates short of an adjacent part of the turbine housing so that there is always a gap between the end of the piston and the adjacent part of the
  • the heat shield enables parts of the turbocharger apparatus to rotate such that an oil outlet of the turbocharger apparatus is always pointing vertically downwards. This gives a good gravity feed of oil back to the engine.
  • the heat shield forms a chamber into which the vanes on the piston project, the chamber being sealed so as to prevent gas leakage to a low pressure side of the turbine.
  • the chamber makes the heat shield very effective at stopping heat passing to the low pressure side of the turbine apparatus.
  • variable turbocharger apparatus is able to be such that the vanes are always in the gas flow to direct the gases at an appropriate angle onto the turbine.
  • the variable turbocharger apparatus may include fork means which engages in a groove in the piston.
  • the fork means enables the piston to be moved backwards and forwards in an axial direction without forcing the piston to one side and thus causing it to bind in the variable turbocharger apparatus.
  • the piston comprises a cylindrical body portion having the groove provided at that end of the body portion remote from the gap.
  • the piston will usually be arranged to slide in a cylindrical part of the turbine housing.
  • the fork means is located on a shaft that is mounted in the housing.
  • the shaft may be connected to an actuator valve which enables movement to be applied to the fork means.
  • the fork means is preferably a bifurcated fork but other types of fork means may be employed.
  • the variable turbocharger apparatus may include an air bleed passage which leads from the outlet for air from the compressor to the actuator valve, the air bleed passage enabling air to be directed against a diaphragm in the actuator valve in order to cause movement of the actuator valve, whereby movement of the actuator valve can be transmitted to the fork means and the piston in dependence upon air bleed pressure.
  • the air bleed pressure will usually be dependent upon the speed of rotation of the compressor.
  • a separate air supply may be used.
  • the separate air supply may be provided by a small separate electronic compressor.
  • micro-processors can be used to monitor a selected parameter or parameters and to compute the position of the piston to give the required piston position.
  • variable turbocharger apparatus may be one in which the piston is provided with a lug which engages a pin for preventing rotation of the piston.
  • the piston will be spring biased to its closed position.
  • the piston is spring biased to its closed position by a single coil spring.
  • the single coil spring is axially positioned inside the actuator valve.
  • more than one spring may be employed.
  • biasing means other than springs may be employed.
  • the variable turbocharger apparatus may include sealing means for forming a sliding seal between the piston and the housing.
  • the sealing means may comprise at least one sealing piston ring.
  • sealing piston ring Preferably, only one sealing piston ring is employed but more than one sealing piston ring may be employed if desired.
  • the or each sealing piston ring may be located in a cylindrical body portion of the piston. Alternatively, the or each sealing piston ring may be mounted in the turbine housing.
  • the end of the piston adjacent the gap may be chamfered. This chamfered end of the piston may help to prevent the build up of products of combustion at this point with some types of engine, for example 2- and 4- stroke petrol driven engines.
  • variable turbocharger apparatus may include at least one bearing against which the sealing means slides backwards and forwards.
  • bearing it is preferred that the bearing be located in the housing adjacent the cylindrical body portion of the piston.
  • the compressor housing and the turbine housing are formed as separate parts. This may facilitate assembly of the variable turbocharger apparatus and it may also facilitate fixing of the variable turbocharger apparatus in various engine compartments of various vehicles.
  • variable turbocharger apparatus may advantageously include a chamber in which the fork means locates, the piston being such as to cover the chamber to prevent a heat build-up on the fork means and to prevent a turbulent gas flow at an exit part of the turbine.
  • variable turbocharger apparatus may be one in which the piston has an end in which is mounted a conical diffuser, the conical diffuser being for facilitating gas extraction from the turbine.
  • variable turbocharger may advantageously be one in which the piston includes at least one solid piston ring.
  • variable turbocharger apparatus may be one in which the heat shield is clamped by clamps between the turbine housing and the bearing housing, and in which the heat shield is rotatable through 360° on loosening of the clamps thereby to enable the turbocharger apparatus to be bolted to different engines at different angles.
  • variable turbocharger apparatus may be one in which the piston is mounted inside the turbine housing such that the piston slides directly over the turbine to allow a large gas exit area. This in effect means that the turbine is so constructed that it does not have a trim part.
  • the present invention also extends to an engine when provided with the variable turbocharger apparatus.
  • the engine may be any general type of engine including diesel and petrol driven engines.
  • variable turbocharger apparatus 2 comprises a compressor housing 64 and a compressor 6.
  • the compressor 6 has blades 8.
  • the compressor 6 is mounted for rotation in the housing 64 by being mounted on a central shaft 10.
  • a turbine 12 is mounted for rotation in a turbine housing 4 by being mounted on the shaft 10.
  • the turbine 12 has blades 14.
  • the housing 64 has a first inlet 16 for enabling air to be conducted to the compressor 6.
  • the housing 64 also has an outlet 18 for air from the compressor.
  • the outlet 18 enables air from the compressor 6 to be conducted to an engine (not shown).
  • the housing 4 has a second inlet 20 for enabling exhaust gases from the engine to be conducted to the turbine 12.
  • a chamber 22 surrounds the turbine 12 and this chamber 22 receives the exhaust gases from the second inlet 20 before the exhaust gases are conducted to the turbine 12.
  • the chamber 22 may be regarded as a volute-shaped toroidal chamber.
  • a piston 24 is positioned between the turbine 12 and the housing 4.
  • the piston 24 is slidable backwards and forwards to form a movable wall separating the turbine 12 from the chamber 22 which surrounds the turbine 12.
  • the piston 24 is such that in its closed position it terminates short an adjacent part 26 of the housing 4 so that there is always a gap 28 between the end 30 of the piston 24 and the adjacent part 26 of the housing 4. This means that exhaust gases from the chamber 22 can always pass through the gap 28 to act on the blades 14 of the turbine 12.
  • the piston 24 is such that in its open position, the gap 28 is increased.
  • the piston 24 is biased to its closed position against pressure from exhaust gases in the chamber 22 during use of the variable turbocharger apparatus 2 so that the piston 24 slides backwards and forwards to vary the gap 28 in dependence upon engine operating conditions.
  • the piston 24 is biased by means of an actuator valve 7.
  • the piston 24 comprises a cylindrical body portion 34 having a groove 36 at that end of the body portion 34 remote from the gap 28.
  • fork means in the form of a bifurcated fork 21 is located in the groove 36.
  • the fork 21 is also fitted to a shaft 54 which can rotate in a bearing housing 68.
  • a metal bar 91 On top of the shaft 54 is a metal bar 91 which is connected to the actuator valve 7.
  • the actuator valve 7 thus acts as control means.
  • the first variable turbocharger apparatus 2 includes sealing means in the form of a sealing piston ring 52.
  • the sealing piston ring 52 is for forming a sliding seal between the piston 24 and the housing 4.
  • the sealing piston ring 52 is located in the turbine housing 66.
  • the sealing piston ring 52 can alternatively be located in the piston 24 as shown by dotted lines 58 in Figure 2.
  • the end 30 of the piston 24 is chamfered as shown so that any products of combustion from the exhaust gases in the chamber 22, which may tend to build up on the part of the piston 24 forming the movable wall, may tend to break away and thus not hinder the sliding movement of the piston 24.
  • the variable turbocharger apparatus 2 includes a heat shield 17.
  • the heat shield 17 has a flange 19.
  • the heat shield 17 is mounted with screws 420 over the bearing housing 68.
  • Figure 5 shows an air gap between the bearing housing 68 and the heat shield 17.
  • a sealing ring may be located in the heat shield 17 as shown in Figure 5 by dotted lines 5.
  • the sealing ring may be located inside the bore of the piston 24, as shown in Figure 1 by dotted lines 75, to operate on the outside of the heat shield 17.
  • the housing 4 is separable into two end parts 64,66 and a central part 68. This may facilitate positioning of the variable turbocharger apparatus 2 in various required positions in various engine compartments in vehicles or in other apparatus.
  • the end part 64 is secured to the central part 68 by means of a cir-clip 70.
  • the end part 66 is secured to the central part 68 by locking washers 72 which are held in position by bolts 74.
  • the end part 64 forms a compressor housing
  • the end part 66 forms a turbine housing
  • the central part 68 forms a bearing housing.
  • the variable turbocharger apparatus 2 is also provided with an oil intake pipe 76 for providing oil for bearings (not shown) on the shaft 10.
  • the shaft 10 is formed with a friction welded head 78 at one end. The other end of the shaft 10 is screw threaded as shown to receive a nut 80, which is effective to hold the compressor 6 in position.
  • An oil return pipe 82 is also provided for enabling the oil provided for the bearings via the oil intake pipe 76 to drain away.
  • the second inlet 20 is provided with a flange 86.
  • the flange 86 has bolt holes 88 so that the flange 86 can be bolted to an exhaust outlet (not shown) of the engine.
  • the compressor 6 is surrounded by a chamber 90 which is somewhat similar to the chamber 22.
  • a seal in the form of an O-ring seal 92 is provided as shown.
  • the exhaust gases from the engine are able to drive the turbine 12 at substantially always the required rate to enable the compressor 6 to provide the amount of air required by the engine from the variable turbocharger apparatus 2, via the outlet 18.
  • the bleeding of air along the air bleed passage 60 is effective to act on the actuator valve 7 to cause the piston 24 to slide towards its open position in which the size of the gap 28 is increased. After the exhaust gases have driven the turbine 12, they are exhausted via an exhaust outlet 94 formed in the housing 4.
  • the piston 24 is provided with an annular groove, shown by the dotted lines 58, for receiving the sealing piston ring 52.
  • the sealing piston ring 52 may be located in the housing 4 as shown in Figure 1.
  • the groove 36 is also shown in Figure 2, for receiving the fork 21.
  • Figures 2, 3 and 4 show that on the piston 24 there is a lug 146 which may have a slot 144 as shown, or a hole (not shown), for location on to a pin 142.
  • the pin 142 may be mounted in the bearing housing 68 as shown, or alternatively in the turbine housing 66.
  • the pin 142 and the lug 146 are provided to prevent rotation of the piston 24.
  • the piston 24 is such that the face 100 of the end 30 is provided with vanes 102.
  • the vanes 102 are oriented so that they direct the incoming gas flow in a tangential direction to provide the appropriate gas flow.
  • the vanes 102 are cut or otherwise provided in the end 30 of the piston 24.
  • Vanes 104 are also provided in the turbine housing 66,the vanes 104 being provided in the form of an insert 31 as shown in Figure 1. Alternatively, the vanes 104 may be cast into the turbine housing 66.
  • the angular positions of the vanes 102,104 in the turbine housing 66 and the piston 24 are such that the vanes 102 on the piston 24 are interposed with the vanes 104 in the turbine housing 66. Relative displacement of the piston 24 varies the extent of overlap of the vanes 102,104.
  • FIG 7 there is shown second variable turbocharger apparatus in which similar parts as in Figure 1 have been given the same reference numerals and will not again be described.
  • the relative positions of the fork 21 and the piston 24 have been changed so that the piston 24 operates in the opposite direction to that shown in Figure 1.
  • Figure 7 also shows how the heat shield 17 is used as an insert to hold the vanes 104.
  • the insert is also shown in Figure 11 and Figure 12.
  • Figures 11 and 12 show respectively an end view and a side view of the heat shield 17, provided with the vanes 104.
  • FIG 8 there is shown third variable turbocharger apparatus in which similar parts as in Figure 7 have been given the same reference numerals and will not again be described.
  • a trim 136 as shown in Figure 7 on the turbine 12 has been removed. This is to allow a larger exit area from the turbine 12.
  • the piston 24 is slightly different in that the piston 24 terminates in a conical diffuser 132.
  • Figure 9 shows fourth variable turbocharger apparatus 2 which is similar to the variable turbocharger apparatus 2 shown in Figure 8 but which employs a longer piston 24 to prevent gases building up in an area 134. Also, turbulent gas flow in the area 134 and turbulent gas flow leading to the outlet of the variable turbocharger apparatus 2 is avoided or reduced.
  • the longer piston 24 of Figure 9 also has the conical diffuser 132.
  • turbocharger apparatus 2 which may be the variable turbocharger apparatus 2 shown in either of Figures 7, 8 or 9. Again similar parts as in the previous Figures have been given the same reference numerals and their precise construction and operation will not again be given.
  • a control arm 91 which terminates in a connection member 140 for connecting to the actuator valve 7.
  • the actuator valve 7 takes pressure from the compressor side of the turbine 12. Alternatively, the pressure may be taken from an engine management system (not shown).
  • Figure 10 also shows a pin 142 which locates in an aperture 144 in a lug 146 formed on the piston 24.
  • the pin 142 acts to stop rotation of the piston 24 during the backwards and forwards sliding movement of the piston 24.
  • the piston 24, the pin 142, the aperture 144 and the lug 146 are shown in more detail in Figures 2 and 3.
  • Figure 10 further shows how the fork 21 has two arms 148, 150.
  • the arm 148 has a pin 152 and the arm 150 has a pin 154.
  • the pins 152, 154 locate in the groove 36 and thus enable the piston 24 to be moved backwards and forwards without putting undue sideways pressure on the piston 24 which could move it out of axial sliding alignment and could thus cause the piston 24 to bind.
  • the fork 21 is attached to a rod 54 which is mounted in the turbine housing 66.
  • the rod 54 connects to the control arm 91 as shown.
  • the slots 10 are provided in the piston 24.
  • the slots 10 receive the vanes 104 and the vanes 104 may extend from an insert.
  • the reverse arrangement may be employed in which the slots are in the insert, and in which the vanes 104 for the slots then project from the piston 24.
  • the slots may be cast in the turbocharger apparatus housing.
  • the slots 10 may be omitted.
  • the slots that may be omitted may thus be in the piston 24 or in the insert 31.
  • the above described variable turbocharger apparatus employs sealing means in the form of a sealing piston ring 52.
  • the sealing means may be a sealing ring other than a split piston ring. Where a split piston ring is employed, this may be inwardly sprung to bear against the outer surface of the piston 24 in order to effect the required seal against gases. Such a split piston ring 52 will rub on the surface of the piston 24 and thus some friction will be created. Whilst this is satisfactory in many circumstances, if it is desired to reduce or obviate this friction, then a solid piston ring may be employed. Because this solid piston ring does not have a split in it, it is not inwardly sprung and thus friction is reduced.
  • variable turbocharger apparatus operates, exhaust gases will be contacting the piston ring.
  • these exhaust gases may cause the split piston ring to operate with a hammering effect on the surface of the piston 24, and this can be disadvantageous and can cause undesirable wear on the surface of the piston 24.
  • the use of the solid piston ring may help to avoid this hammering effect and may thus again reduce undesirable wear on the surface of the piston 24.
  • the piston ring may be advantageous to produce the piston ring from a material which has substantially the same rate of expansion as the material from which the piston 24 is produced.
  • the piston 24 and the piston ring can expand at substantially the same rate to avoid creating unnecessary friction as might be the case if the piston 24 expanded more than the piston ring.
  • the piston 24 and the piston ring can be made of the same or different materials.
  • FIG. 16 and 17 a second vane arrangement is shown in which the heat shield 17 is replaced by a heat shield 201.
  • the heat shield 201 has a chamber 203 at the back of the heat shield 201.
  • the chamber 203 is preferably a sealed unit along a face 320.
  • Figures 18, 19 and 20 illustrate the heat shield 201.
  • Figure 18 is an end view which shows the heat shield 201 with the vanes 102 entering slots 260 in the heat shield 201.
  • Figure 19 shows the vanes 102 in the open position, whilst Figure 20 shows the vanes 102 in the closed position.
  • the movement of the piston 24 on this second vane arrangement is the same as described above with reference to Figures 7, 8 and 9.
  • the turbocharger apparatus shown in Figures 16 to 20 gives the following advantages.
  • vanes 102, 104 may take a different shape to those shown, and more or less vanes than those shown may be employed. If desired, the vanes may be reversed to allow a reverse rotation of the turbine 12.
  • variable turbocharger apparatus 2 may be produced in various sizes commensurate with the size of engine to which the variable turbocharger apparatus 2 is to be fitted.
  • the shape of the housing 4 can be varied as may be desired. Water cooled bearings may be incorporated.
  • the housing 4 and the various components within the housing 4 can be made of any desired and suitable materials. Also, sealing rings may be added or dispensed with as desired.

Claims (9)

  1. Veränderlicher Turbolader (2), der ein Verdichtergehäuse (64), einen Verdichter (6), der drehbar in dem Verdichtergehäuse (64) angebracht ist, ein Turbinengehäuse (4), eine Turbine (12), die drehbar in dem Turbinengehäuse (4) angebracht ist, einen ersten Einlaß (16), um zu ermöglichen, daß Luft zum Verdichter (6) geleitet wird, einen Auslaß (18) für Luft vom Verdichter (6), einen zweiten Einlaß (20), um zu ermöglichen, daß Auspuffgase von einem Motor zur Turbine geleitet werden, eine Kammer (22), die die Turbine (12) umgibt und die die Auspuffgase aus dem zweiten Einlaß (20) aufnimmt, bevor die Auspuffgase zu der Turbine (12) geleitet werden, einen Kolben (24), der zwischen der Turbine (12) und dem Turbinengehäuse (4) angeordnet ist und der gleitend rückwärts und vorwärts bewegt werden kann, um eine bewegliche Wand, die die Turbine (12) von der Kammer (22), die die Turbine (12) umgibt, trennt, zu bilden, eine Lageranordnung, um die Drehung des Kompressors (6) und der Turbine (12) zu erlauben, und einen Hitzeschild (201), um die Lageranordnung von den Auspuffgasen abzuschirmen, aufweist, wobei der Kolben (24) eine Mehrzahl von Leitschaufeln (102) hat, wobei der Kolben (24) so angeordnet und ausgebildet ist, daß er in seiner geschlossenen Stellung kurz vor einem benachbarten Teil des Turbinengehäuses endet, derart, daß immer eine Öffnung zwischen dem Ende des Kolbens (24) und dem benachbarten Teil des Turbinengehäuses (4) vorhanden ist, wodurch Auspuffgase von der Kammer (22) immer durch die Öffnung hindurchgehen können, um auf die Turbine (12) zu wirken, wobei der Kolben (24) so angeordnet und ausgebildet ist, daß in seiner offenen Stellung die Öffnung vergrößert ist, und wobei der Kolben (24) in seine geschlossene Stellung gegen Druck von Auspuffgasen in der Kammer (22) während der Benutzung des veränderlichen Turboladers (2) vorgespannt ist, wodurch der Kolben (24) rückwärts und vorwärts gleitet, um die Öffnung in Abhängigkeit von Motorbetriebszuständen zu verändern,
    dadurch gekennzeichnet, daß der veränderliche Turbolader (2) derart angeordnet und ausgebildet ist, daß die Leitschaufeln (102) auf dem Kolben (24) in Schlitze (260) in dem Hitzeschild (201) eintreten und dadurch in eine Kammer (203) in dem zusammengebauten Zustand des Turboladers hineinragen, die Kammer (203) einen Endbereich des Lagergehäuses umgibt, und die Leitschaufeln (102) so angeordnet und ausgebildet sind, daß sie immer durch die Schlitze (260) und in die Kammer (203) eingesetzt werden können zur Erleichterung des Zusammenbaus des veränderlichen Turboladers (2).
  2. Veränderlicher Turbolader nach Anspruch 1, und eine Gabeleinrichtung (21) aufweisend, die in eine Nut (36) in dem Kolben eingreift.
  3. Veränderlicher Turbolader nach Anspruch 2, bei dem die Gabeleinrichtung (21) auf einer Welle (54) angeordnet ist, die in dem Turbinengehäuse (4) angebracht ist.
  4. Veränderlicher Turbolader nach Anspruch 3, bei dem die Welle (54) mit einem Betätigungsventil (7) verbunden ist.
  5. Veränderlicher Turbolader nach Anspruch 3 oder Anspruch 4, und eine Kammer aufweisend, in der die Gabeleinrichtung (21) sitzt, wobei der Kolben (24) so ausgebildet und angeordnet ist, daß er die Kammer abdeckt, um einen Hitzestau auf der Gabeleinrichtung (21) zu verhindern und einen turbulenten Gasfluß bei einem Ausgangsteil der Turbine (12) zu verhindern.
  6. Veränderlicher Turbolader nach einem der vorhergehenden Ansprüche, bei dem der Kolben (24) mit einem Ansatz (146) versehen ist, der an einem Bolzen (142) angreift, um eine Drehung des Kolbens zu verhindern.
  7. Veränderlicher Turbolader nach einem der vorhergehenden Ansprüche, bei dem der Kolben ein Ende hat, in dem ein konischer Diffusor (132) angebracht ist, wobei der konische Diffusor (132) zur Erleichterung des Gasabzugs von der Turbine (12) bestimmt ist.
  8. Veränderlicher Turbolader nach einem der vorhergehenden Ansprüche, bei dem der Kolben (24) mindestens einen festen Kolbenring (52) aufweist.
  9. Veränderlicher Turbolader nach einem der vorhergehenden Ansprüche, bei dem der Kolben (24) derart innerhalb des Turbinengehäuses (4) angebracht ist, daß der Kolben (24) direkt über der Turbine (12) gleitet, um einen großen Gasausgangsbereich zu erlauben.
EP95107138A 1988-05-27 1989-05-26 Turbolader Expired - Lifetime EP0678657B1 (de)

Applications Claiming Priority (11)

Application Number Priority Date Filing Date Title
GB888812664A GB8812664D0 (en) 1988-05-27 1988-05-27 Turbocharger apparatus
GB8812664 1988-05-27
GB8817230 1988-07-20
GB888817230A GB8817230D0 (en) 1988-07-20 1988-07-20 Turbocharger apparatus
GB888827153A GB8827153D0 (en) 1988-11-21 1988-11-21 Turbocharger apparatus
GB8827153 1988-11-21
GB888827761A GB8827761D0 (en) 1988-11-28 1988-11-28 Turbocharger apparatus
GB8827761 1988-11-28
GB8901803 1989-01-27
GB898901803A GB8901803D0 (en) 1989-01-27 1989-01-27 Turbocharger apparatus
EP89906165A EP0442884B1 (de) 1988-05-27 1989-05-26 Turbolader

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP89906165A Division EP0442884B1 (de) 1988-05-27 1989-05-26 Turbolader
EP89906165.9 Division 1989-05-26

Publications (3)

Publication Number Publication Date
EP0678657A2 EP0678657A2 (de) 1995-10-25
EP0678657A3 EP0678657A3 (de) 1995-11-22
EP0678657B1 true EP0678657B1 (de) 1998-11-25

Family

ID=27516817

Family Applications (2)

Application Number Title Priority Date Filing Date
EP89906165A Expired - Lifetime EP0442884B1 (de) 1988-05-27 1989-05-26 Turbolader
EP95107138A Expired - Lifetime EP0678657B1 (de) 1988-05-27 1989-05-26 Turbolader

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP89906165A Expired - Lifetime EP0442884B1 (de) 1988-05-27 1989-05-26 Turbolader

Country Status (6)

Country Link
EP (2) EP0442884B1 (de)
AT (2) ATE135440T1 (de)
AU (1) AU3693089A (de)
DE (2) DE68925977T2 (de)
GB (1) GB9206950D0 (de)
WO (1) WO1989011583A1 (de)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4232400C1 (de) * 1992-03-14 1993-08-19 Mercedes-Benz Aktiengesellschaft, 7000 Stuttgart, De
DE4215301A1 (de) * 1992-05-09 1993-11-11 Mak Maschinenbau Krupp Abgasturbolader mit einer Radialturbine
EP0571205B1 (de) * 1992-05-21 1997-03-05 Alliedsignal Limited Regelbarer Turbolader
GB9222133D0 (en) * 1992-10-21 1992-12-02 Leavesley Malcolm G Turbocharger apparatus
US5443362A (en) * 1994-03-16 1995-08-22 The Hoover Company Air turbine
DE19615237C2 (de) * 1996-04-18 1999-10-28 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
DE19805476C1 (de) * 1998-02-11 1999-10-07 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
DE19816645B4 (de) 1998-04-15 2005-12-01 Daimlerchrysler Ag Abgasturboladerturbine
EP1247012B1 (de) 2000-01-14 2004-05-12 Honeywell Garrett SA Turbolader mit verschiebbaren leitschaufeln, hitzeschild und einer abnehmbaren, axialen betätigungsvorrichtung
DE60032523T2 (de) 2000-11-30 2007-11-22 Honeywell Garrett S.A. Abgasturbolader mit variabler Geometrie und einem Ringschneider
ITTO20010506A1 (it) 2001-05-25 2002-11-25 Iveco Motorenforschung Ag Turbina a geometria variabile.
ITTO20010505A1 (it) 2001-05-25 2002-11-25 Iveco Motorenforschung Ag Turbina a geometria variabile.
GB0227473D0 (en) 2002-11-25 2002-12-31 Leavesley Malcolm G Variable turbocharger apparatus with bypass apertures
US7581394B2 (en) * 2003-12-10 2009-09-01 Honeywell International Inc. Variable nozzle device for a turbocharger
GB2427446B (en) * 2005-06-20 2010-06-30 Malcolm George Leavesley Variable turbocharger apparatus
US8123470B2 (en) * 2007-08-10 2012-02-28 Honeywell International Inc. Turbine assembly with semi-divided nozzle and half-collar piston
AT505407B1 (de) * 2007-08-16 2009-01-15 Ghm Engineering Abgasturbolader für eine brennkraftmaschine
GB0811228D0 (en) * 2008-06-19 2008-07-30 Cummins Turbo Tech Ltd Variable geometric turbine
GB201015679D0 (en) 2010-09-20 2010-10-27 Cummins Ltd Variable geometry turbine
GB201119386D0 (en) 2011-11-10 2011-12-21 Cummins Ltd A variable geometry turbine
GB2585634A (en) * 2019-05-14 2021-01-20 Cummins Ltd Turbine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1074206B (de) * 1958-01-20 1960-01-28 Gebrüder Sulzer Aktiengesellschaft, Winterthur (Schweiz) Leitrad für Turbomaschinen
NL121768C (de) * 1964-05-11
EP0034915A1 (de) * 1980-02-22 1981-09-02 Holset Engineering Company Limited Radial nach innen durchströmte Turbinen
US4403914A (en) * 1981-07-13 1983-09-13 Teledyne Industries, Inc. Variable geometry device for turbomachinery
DE3244190A1 (de) * 1981-12-24 1983-10-20 Daimler-Benz Ag, 7000 Stuttgart Radialturbine
DE3375419D1 (en) * 1982-04-29 1988-02-25 Bbc Brown Boveri & Cie Turbo charger with a sliding ring valve

Also Published As

Publication number Publication date
DE68925977T2 (de) 1996-10-24
ATE135440T1 (de) 1996-03-15
EP0678657A3 (de) 1995-11-22
WO1989011583A1 (en) 1989-11-30
DE68925977D1 (de) 1996-04-18
EP0678657A2 (de) 1995-10-25
DE68928865T2 (de) 1999-07-01
GB9206950D0 (en) 1992-05-13
EP0442884B1 (de) 1996-03-13
EP0442884A1 (de) 1991-08-28
DE68928865D1 (de) 1999-01-07
ATE173794T1 (de) 1998-12-15
AU3693089A (en) 1989-12-12

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