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
  • F02B47/00—Methods of operating engines involving adding non-fuel substances or anti-knock agents to combustion air, fuel, or fuel-air mixtures of engines
  • F02B47/04—Methods of operating engines involving adding non-fuel substances or anti-knock agents to combustion air, fuel, or fuel-air mixtures of engines the substances being other than water or steam only
  • F02B47/08—Methods of operating engines involving adding non-fuel substances or anti-knock agents to combustion air, fuel, or fuel-air mixtures of engines the substances being other than water or steam only the substances including exhaust gas
• • 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
  • F01D9/00—Stators
  • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
  • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
  • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
  • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
  • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
  • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
• • 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
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
  • F01D11/005—Sealing means between non relatively rotating elements
• • 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
  • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
• • 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 invention relates to an exhaust gas turbocharger specified in the preamble of claim 1. Art.
• EP 2 348 195 A2 discloses an exhaust gas turbocharger with a turbine comprising a turbine housing and with a bearing housing.
• the exhaust gas turbocharger also includes a turbine housing and the bearing housing separately formed guide with two insert elements.
• One of the insert elements is a carrier element.
• the other of the insert elements is a cover element.
• the insert elements are to form a flow channel between the insert elements in the axial direction of the
• Exhaust gas turbocharger spaced from each other.
• guide vanes of the guide are mounted relative to the insert elements movable.
• the insert element which is more closely associated with a turbine outlet of the turbine, has a first wall area extending at least substantially in the radial direction and an adjoining one, at least substantially in the axial direction
• the wall regions form a corner region of the insert element.
• the second wall region has a circumferential groove in which a sealing element is accommodated.
• WO 2007/046798 A1 also has such an exhaust gas turbocharger. Also that of the insert elements of the exhaust gas turbocharger, which is assigned to the turbine outlet closer, has in its second wall region two grooves in which respective sealing elements are arranged.
• Patent claim 1 solved.
• Advantageous embodiments with expedient and non-trivial developments of the invention are specified in the remaining claims.
• Such an exhaust gas turbocharger comprises at least one housing part, on which at least partially one of the housing part, in particular of all housing parts of the
• Exhaust gas turbocharger separately formed guide is arranged.
• the guide comprises two insert elements, which are spaced apart from each other in the axial direction to form a flow channel between the insert elements.
• the insert elements limit the flow channel in the axial direction of the exhaust gas turbocharger.
• the guide comprises vanes, which at least at one of
• Insert elements are mounted movable relative to the insert elements.
• Guide vanes serve to divert or deflect the exhaust gas flowing through the flow channel.
• At least one first of the insert elements has at least one, at least substantially in the radial direction of the exhaust gas turbocharger extending first
• the wall regions form a corner region of the insert element.
• the first insert element is thus adapted accordingly in terms of its geometry or its outer contour to exposures of the first insert element with high temperatures during operation of the exhaust gas turbocharger, so that the first insert element is not or only slightly deformed.
• the risk of jamming and / or any other malfunction of the movable relative to the insert elements vanes is thus avoided or kept very low. Functional gaps between the vanes and the insert elements can be kept very low, so that the
• Exhaust gas flowing through the flow channel can not flow past the guide vanes or only in very small amounts and a turbine wheel of a turbine of the exhaust gas turbocharger can flow in an undirected manner.
• At least substantially all of the exhaust gas flowing through the flow channel can be flow-effectively discharged by means of the guide vanes.
• the exhaust gas turbocharger can be designed in particular as a reciprocating internal combustion engine
• the recess has a bottom, which is opposite to a first
• the recess is set back.
• the recess is limited to at least three sides.
• the recess may for example be formed as a groove whose corners may be rounded.
• the first insert element preferably has the at least one recess in the first wall region and at least one second recess in the corner region. This leads to a particularly small deformation of the first insert element, which benefits the functional reliability and the efficient operation of the exhaust gas turbocharger according to the invention.
• the recess serves not only to illustrate the advantageous deformation behavior of the first insert element but also for receiving and securing the sealing element. This keeps the costs of the exhaust gas turbocharger according to the invention in a small framework.
• the housing part is a
• Turbine housing of the turbine of the exhaust gas turbocharger is subjected to very high temperatures during operation of the exhaust gas turbocharger, since it is flowed through by exhaust gas of the internal combustion engine.
• the first insert element is arranged in particularly close proximity to the turbine housing, the risk of a very high temperature exposure of the first insert element of the turbine housing is relatively high, if no corresponding countermeasures are taken.
• the at least one recess at least minimizes thermally induced deformations of the first insert element.
• the exhaust gas turbocharger may also be connected to the turbine housing
• Bearing housing include, on or in which at least partially a rotor of the exhaust gas turbocharger is mounted.
• the rotor comprises the turbine wheel and a shaft with which the turbine wheel is rotatably connected.
• the exhaust gas turbocharger may further comprise a compressor with a compressor housing, in which at least partially a compressor wheel is arranged. Also, the compressor is associated with the rotor and rotatably connected to the shaft. The rotor is about an axis of rotation relative to the bearing housing, relative to the Compressor housing and rotatable relative to the turbine housing. As a result of the rotationally fixed connections, the compressor wheel can be driven via the turbine wheel and compress the air supplied to the internal combustion engine.
• the housing part is partially received in the recess.
• the guide device is preferably fastened exclusively via one of the insert elements, in particular exclusively via the second insert element, to a housing part, in particular to the bearing housing, of the exhaust gas turbocharger. This attachment of the guide allows the realization of only a relatively small
• the insert elements are connected to each other by means of at least one connecting element.
• the connecting element may be formed separately from the insert elements, whereby a simple mounting of the guide is made possible.
• about the connecting element is that of the
• Insert elements which is not attached to a housing part of the exhaust gas turbocharger, on that of the insert elements, which on a housing part of the
• Exhaust gas turbocharger is attached, held.
• the guide can be stored relative to the housing part or the housing part of the exhaust gas turbocharger and precisely aligned.
• the first insert element is spaced from the housing part. Heat transfer from the housing part to the first
• Insert element can be kept so low, so that there is only very small, thermally induced deformations of the first insert element.
• the entire guide is spaced from the housing part, in particular from all housing parts, of the exhaust gas turbocharger.
• only very small function gaps can be realized, which is accompanied by a particularly efficient and efficient operation of the exhaust gas turbocharger.
• FIG. 1 shows a detail of a schematic longitudinal sectional view of a turbine of an exhaust gas turbocharger, with a turbine housing, in which a guide device for discharging exhaust gas flowing through the turbine housing is arranged;
• FIG. 1 shows a turbine 10 of an exhaust-gas turbocharger for an internal combustion engine designed, for example, as a reciprocating internal combustion engine.
• the turbine 10 comprises a turbine housing 12, which has at least one feed channel 14.
• the turbine housing 12 further has a receiving space in which a turbine wheel of the turbine 10 is at least partially rotatably received about an axis of rotation relative to the turbine housing 12.
• the exhaust gas turbocharger further comprises a bearing housing, not shown in FIG. 1, which adjoins the turbine housing 12 in the axial direction of the exhaust gas turbocharger and is connected to the turbine housing 12.
• a rotor of the exhaust gas turbocharger is rotatable about the axis of rotation relative to the bearing housing stored.
• the rotor comprises a shaft with which the turbine wheel is rotatably connected.
• the exhaust gas turbocharger comprises a compressor with a
• Compressor housing which adjoins the bearing housing in the axial direction of the exhaust gas turbocharger and is connected thereto.
• the compressor housing has a further receiving space in which a compressor wheel of the compressor is at least partially rotatably received about the axis of rotation relative to the compressor housing.
• the compressor is also associated with the rotor and rotatably connected to the shaft.
• the compressor can be driven by the turbine and compress the internal combustion engine air supplied.
• the internal combustion engine with compressed air can be supplied and efficiently driven, resulting in only low fuel consumption and thus low C0 2 emissions.
• the exhaust gas turbocharger also includes a guide 16, which in the
• the guide 16 includes a first
• the guide device 16 further comprises a second insert element, which is referred to as a carrier element 20.
• the cover member 18 and the support member 20 are - as shown in FIG. 1 can be seen - in the axial direction of the turbine 10 and thus of the exhaust gas turbocharger with formation of a flow channel 22 between the cover 18 and the support member 20 spaced from each other. In other words, that limits
• the cover element 18 is also referred to as a counter contour element or contour element, since it has, at least in some areas, a mating contour which corresponds at least essentially to an outer contour of the turbine wheel.
• the feed channel 14 extends, for example, in the circumferential direction of the turbine wheel over its circumference at least substantially helically and is fluidly connected to at least one combustion chamber, in particular a cylinder, of the internal combustion engine.
• exhaust gas of the internal combustion engine can flow from the combustion chamber into the feed channel 14.
• the feed channel 14 is fluidly connected to the flow channel 22 so that the exhaust gas can flow from the feed channel 14 into the flow channel 22.
• Flow channel 22 opens into the receiving space for the turbine wheel, so that the exhaust gas flowing through the flow channel 22 can flow to the turbine wheel and thereby drive.
• the guide 16 also includes at least partially arranged in the flow channel 22 and not shown in FIG. 1 guide vanes, which are arranged distributed in the circumferential direction of the turbine wheel over its circumference.
• the guide vanes are used for diverting or deflecting the exhaust gas flowing through the flow channel 22, so that the exhaust gas is the turbine wheel in at least one streamlined
• the vanes are only on the support member 20 relative to
• the turbine 10 can be adapted to different exhaust gas mass flows. This allows the turbine 10 both at low
• the cover 18 has a first recess 24 and a second recess 26 a the turbine housing 12 facing and the flow channel 22 facing away from 27 of the cover 18.
• the first recess 24 is arranged in a corner region 28 of the cover element 18.
• the presently rounded corner region 28 is characterized by a first wall region 30 extending at least substantially in the radial direction and an adjoining one, at least in the
• the second wall portion 32 of the cover 18 is formed.
• the second recess 26 is arranged in the first wall region 30.
• the recesses 24, 26 are formed at least substantially groove-shaped or groove-like and limited in each case on three sides.
• the first recess 24 has a first base 34, which adjoins a first surface 36 of a first wall part 38, to which the first recess 24 adjoins, and a second surface 40 of a second wall part 42 of the first recess 24 adjoining the first recess 24 Cover member 18 of the
• Turbine housing 2 is set back away. Similarly, a second bottom 44 of the second recess 26 opposite the second surface 40 of the second
• Turbine housing 12 set back away.
• the recesses 24, 26 is thus the wall thickness of the cover member 18 in comparison to the recesses 24, 26 respectively subsequent wall parts 38, 42, 48 reduced.
• the cover element 18 On a further side 50 facing away from the side 27, on which the cover element 18 at least partially delimits the flow channel 22, the cover element 18 is at least substantially planar, ie. the cover 18 has on the other side 50 no recess. This realizes a flow-favorable guidance of the flow channel 22 by flowing exhaust gas.
• the cover member 18 is completely spaced from the turbine housing 12. This means that the cover member 18 does not touch the turbine housing 12.
• a sealing member 52 is provided in the form of a V-seal.
• the sealing element 52 could also be formed in the form of a U-seal as well.
• the sealing element 52 is supported on the one hand on the turbine housing 12 and on the other hand on the cover 18.
• the turbine housing 12 projects partially into the second recess 26.
• the sealing element 52 is at least partially supported on the projecting into the second recess 26 part of the turbine housing 12.
• FIG. 2 shows a further embodiment of the turbine 10 according to FIG. 1.
• the fastening of the guide device 16 on the turbine housing 12 is explained with reference to FIG.
• the attachment of the guide 16 on the turbine housing 2 is preferably carried out only via the support member 20 which is fixed to the turbine housing 12. This means that the cover 18 is not attached to the turbine housing 12 and not on the bearing housing and not on the compressor housing.
• the carrier element 20 is on the turbine housing 12, but not on the bearing housing and not on
• Compressor housing attached.
• the cover member 18 is over at least one
• Connecting element 54 which in the present case is a bolt, held on the carrier element 20.
• the fastening and the positional securing of the cover element 18 relative to the turbine housing 12 or to all housing parts of the exhaust gas turbocharger thus takes place via the carrier element 20, which is secured in position relative to all housing parts of the exhaust gas turbocharger as a result of its attachment to the turbine housing 12.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Combustion & Propulsion (AREA)
• Chemical Kinetics & Catalysis (AREA)
• General Chemical & Material Sciences (AREA)
• Supercharger (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Applications Claiming Priority (2)

Publications (1)

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ID=47594629

Family Applications (1)

Country Status (6)

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Family Cites Families (12)

• 2012
  • 2012-01-18 DE DE102012006711A patent/DE102012006711A1/de not_active Withdrawn
• 2013
  • 2013-01-08 CN CN201380005921.0A patent/CN104053864A/zh active Pending
  • 2013-01-08 JP JP2014552561A patent/JP2015504135A/ja not_active Abandoned
  • 2013-01-08 EP EP13700611.0A patent/EP2805027A1/de not_active Withdrawn
  • 2013-01-08 WO PCT/EP2013/000021 patent/WO2013107611A1/de active Application Filing
• 2014
  • 2014-07-06 US US14/324,196 patent/US20140322005A1/en not_active Abandoned

Non-Patent Citations (1)

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