EP2937521A1 - Turbine à géométrie variable avec canal de dérivation pour turbocompresseur à gaz d'échappement - Google Patents

Turbine à géométrie variable avec canal de dérivation pour turbocompresseur à gaz d'échappement Download PDF

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Publication number
EP2937521A1
EP2937521A1 EP14165847.6A EP14165847A EP2937521A1 EP 2937521 A1 EP2937521 A1 EP 2937521A1 EP 14165847 A EP14165847 A EP 14165847A EP 2937521 A1 EP2937521 A1 EP 2937521A1
Authority
EP
European Patent Office
Prior art keywords
turbine
guide blade
face plate
guide
bearing pin
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.)
Withdrawn
Application number
EP14165847.6A
Other languages
German (de)
English (en)
Inventor
Kanagaraj Thangavelu
Deepak Hassan Mallappa
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.)
BMTS Technology GmbH and Co KG
Original Assignee
Bosch Mahle Turbo Systems GmbH and Co KG
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 Bosch Mahle Turbo Systems GmbH and Co KG filed Critical Bosch Mahle Turbo Systems GmbH and Co KG
Priority to EP14165847.6A priority Critical patent/EP2937521A1/fr
Publication of EP2937521A1 publication Critical patent/EP2937521A1/fr
Withdrawn legal-status Critical Current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
    • F01D17/16—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
    • 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
    • F01D17/105—Final actuators by passing part of the fluid
    • 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 a turbine for an exhaust gas turbocharger and to an exhaust gas turbocharger having such a turbine.
  • the invention furthermore relates to a guide blade for such a turbine.
  • the invention relates to an internal combustion engine having such an exhaust gas turbocharger.
  • a so-called waste gate is often employed. This can be used to regulate the charge pressure in the case of turbochargers for internal combustion engines.
  • An alternative to this concept are adjustable guide blades, which allow a variation of the inflow of exhaust gas to the turbine wheel of the turbine part of the exhaust gas turbocharger by means of adjustable guide blades.
  • adjustable guide blades are generally also called variable turbine geometry ("VTG"). Said adjustability allows an optimal adaptation of the flow of exhaust gas onto the turbine wheel as a function of the exhaust gas quantity currently entering the turbine.
  • Adjusting the guide blades into a first position with maximum flow cross section for the case of a large exhaust gas quantity ensures that the exhaust gas molecules do not strike the turbine wheel with too high a velocity.
  • adjusting the guide blades into a second position with minimum flow cross-section results in an acceleration of the exhaust gas molecules. As a result, fewer gas molecules strike the turbine wheel however with increased velocity, resulting in the turbine wheel being accelerated.
  • the basic idea of the invention is to provide a bypass line in the turbine housing of a turbine equipped with variable turbine geometry, via which at least a part of the exhaust gas flow entering the turbine housing can be conducted past the turbine wheel when required.
  • Said bypass line in this case is closed off through the guide blades of the variable turbine geometry or, if required, opened for exhaust gas to flow through.
  • a plurality of guide blades of said variable turbine geometry which are connected upstream of the turbine wheel are adjustable in the known manner between a first position, in which a flow cross-section between the guide blades is maximal for the throughflow of exhaust gas and a second position, in which this flow cross-section is minimal.
  • a design of the guide blades in such a manner that at least one guide blade in the first position opens the bypass line and closes it in the second position is substantial to the invention.
  • the guide blade concerned thus follows the operational principle of a waste gate valve.
  • Undesirably high acceleration of the turbine wheel because of too high an exhaust gas mass flow, the gas molecules of which moreover have too high a gas velocity, and too high a turbine output which is connected to this is thereby avoided.
  • the turbine according to the invention thus combines within it the advantages of a variable turbine geometry and a waste gate device mentioned at the outset, which in this case is realised in the form of said bypass line.
  • the bypass line is designed in such a manner that it is closed off by all guide blades when these are in the first position.
  • the bypass line which is substantial to the invention can be composed of multiple bypass channels which are fluidically connected in parallel with one another. If the number of channels corresponds to the number of guide blades which are present in the turbine, each individual guide blade can be assigned exactly one bypass channel. Thus, each guide blade assumes the function of a waste gate valve for the bypass channel assigned to it.
  • the at least one guide blade is designed in such a manner that it opens the bypass channel only in the first position. In other words, if said guide blade is moved out of the first position this results in a closing of the bypass line or of the bypass channels. In this case, the guide blades follow the operational principle of a conventional variable turbine geometry without additional waste gate device.
  • third position corresponds to the flow cross-section that can be maximally made available by the variable turbine geometry with closed bypass line.
  • this flow cross-section is at least slightly smaller than that with opened bypass line, i.e. said third position is an intermediate position between the first position of the guide blades and the second position, which is accompanied by the minimal flow cross-section.
  • bypass line comprises a number of bypass channels which are connected fluidically in parallel with one another, which corresponds to the number of guide blades.
  • each bypass channel can be individually assigned a guide blade in such a manner that each guide blade opens the bypass channel assigned to it in the first position, closing it in the second position.
  • Each individual bypass channel rather has a channel cross-section which compared to the line cross-section of the entire bypass line is greatly reduced. In other words, the sum of all channel cross-sections corresponds to the line cross-section of the bypass line.
  • no major design changes will then have to be carried out in order to form these as valve for the bypass line as will still be discussed in more detail in the following.
  • Modern turbines for exhaust gas turbochargers are typically designed in the manner of a radial turbine with a radial fluid inlet and an axial fluid outlet.
  • the bypass channels are arranged along the axial direction of the turbine, which is defined by the axis of rotation of the turbine wheel.
  • the bypass channel is thus arranged at least in sections, preferentially completely, parallel to an axis of rotation about which the respective guide blade is rotationally adjustable between the first and the second position. This permits integrating the respective bypass channel into a conventional turbine with variable turbine geometry without major design changes having to be performed on said turbine.
  • the guide blade comprises a guide blade leaf which is attached in a rotationally fixed manner to a bearing pin extending along an axial direction
  • the flow cross-section can be adjusted in the known manner.
  • a closure element is provided on the bearing pin or the guide blade leaf, which is arranged in the respective bypass channel.
  • the closure element in turn is provided with a passage opening in such a manner that said passage opening in the first position of the guide blade is arranged in the bypass channel so that the closure element opens the bypass channel for exhaust gas to flow through.
  • said passage opening is arranged outside the bypass channel when the guide blade is moved away from the first position to the second position.
  • the bypass channel is closed off by the closure element.
  • the bearing pins of the individual guide blades can each be rotatably mounted on a blade bearing ring which is attached in a fixed location on the turbine housing.
  • the adjusting mechanism for adjusting the guide blades between the first and the second position can be realised through the rotational movement of the guide blade which is required anyhow in the known manner for adjusting the flow cross-section.
  • Adjusting the guide blades between the first and the second position in this scenario takes place through rotational adjusting of the bearing pin and of the guide blade leaf attached thereon about an axis of rotation defined through the centre longitudinal axis of the bearing pin. Consequently, no separate adjusting mechanism for the guide blades for opening and closing off the bypass channels is required. This results in cost advantages in the production of the turbine according to the invention.
  • the closure element is formed as a face plate, which is provided at the axial face end on the bearing pin or on the guide blade leaf.
  • Conventional guide blades can be complemented in a simple design manner by such a face plate which itself can be produced in a simple manner.
  • said face plate can be formed cylindrically and arranged concentrically to the bearing pin.
  • the passage opening penetrates the cylindrical face plate along the common axial direction of the face plate and of the bearing pin.
  • bypass channels in parallel with and adjacent to the bearing pin. If the cylindrical face plate is provided with a larger diameter than the bearing pin, the face plate with suitable dimensioning and arrangement relative to the bypass channel and bearing pin projects into the bypass channel. If the passage opening, with respect to a top view of the face plate, is now provided eccentrically on said face plate in a suitable location, a rotation of the bearing pin and of the face plate fastened thereto brings about that the passage opening through a rotational movement of the guide blade for releasing the bypass channel can be moved into said bypass channel and for closing off, back out of said bypass channel again.
  • passage opening is formed as a recess provided on the circumferential side of the cylindrical face plate.
  • a common fastening ring which is arranged concentrically to the turbine wheel.
  • Said fastening ring can comprise on a first face end facing the guide blades for each closure element or for each face plate a recess which is formed complementarily to the closure element or to the face plate, in which the closure element or the face plate can be at least partially received.
  • bypass channels of the bypass line in the turbine housing can each have a cylindrical geometrical shape. In terms of production, the bypass channels can thus be introduced into the turbine housing in a simple manner in the form of bores.
  • the invention furthermore relates to a guide blade for the turbine explained above.
  • the invention furthermore relates to an exhaust gas turbocharger having a turbine with one or multiple of the features mentioned above.
  • the invention also relates to an internal combustion engine having such an exhaust gas turbocharger.
  • FIG. 1 illustrates an example of a turbine 1 according to the invention for an exhaust gas turbocharger, which in the example of the Figures is embodied as a so-called radial turbine, in a longitudinal section.
  • the turbine 1 has a turbine housing 2 with an inlet opening, which is not evident in the longitudinal section of Figure 1 , and an outlet opening 4.
  • the turbine housing 2 surrounds a housing interior space 5, through which exhaust gas expelled from an internal combustion engine flows.
  • a turbine wheel 3 with a shaft 6 is arranged, through which an axis of rotation D of the turbine wheel 3 is defined.
  • the axis of rotation D extends along an axial direction A of the turbine 1, which separates the housing interior space into a high-pressure region 7 formed as a volute and which is in fluid connection with the inlet opening and a low-pressure region 8 which is in fluid connection with the outlet opening 4.
  • a bypass line 9 is furthermore provided, which comprises multiple bypass channels 10, of which in the longitudinal section of Figure 1 only two such channels 10 are shown.
  • the turbine 1 comprises a variable turbine geometry 11, the substantial components of which are shown in Figure 2 in a separate and schematic representation.
  • the variable turbine geometry 11 comprises a plurality of guide blades 12. Connected upstream of the turbine wheel 3, which can be adjustably mounted on a conventional guide blade bearing ring 19 familiar to the relevant person skilled in the art.
  • Such a guide blade 12 is exemplarily shown in a separate representation in Figure 5 , wherein Figure 5a shows a top view of the guide blade 12 and Figure 5b and a longitudinal section.
  • the guide blade 12 has a guide blade leaf 13, which is attached in a rotationally fixed manner to a bearing pin 14 which extends along an axial direction A.
  • a bearing pin 14 which extends along an axial direction A.
  • each bypass channel 10 is assigned to a certain guide blade 12, i.e. the number of guide blades 12 corresponds to that of the bypass channels 10. It is evident, in addition, that the bypass channels 10 each have a cylindrical geometry in the manner of a bore and extend along the axial direction A of the turbine housing 2 in the same.
  • each guide blade 12 has a closure element 15 in the form of a cylindrical face plate 16 which is shown in Figure 5 , which is arranged concentrically to the bearing pin 14 and is attached to the bearing pin 14 on the end face.
  • the face plate 16 may also be attached to the guide blade leaves 13.
  • Each face plate 16 is provided with a passage opening 17, which with respect to the top view of the guide blade 12 shown in Figure 5a is eccentrically arranged on the same in the axial direction A.
  • the passage opening 17 is formed as a recess provided on the circumferential side 18 of the face plate 16 (see Fig. 5a ).
  • the passage opening 17 penetrates the cylindrical face plate 16 along the axial direction A.
  • Figure 1 shows the guide blades 12 in a first position, in which they open the bypass channels 10 for exhaust gas to flow through. In the first position, the face plate 16 projects into the bypass channel 10 in such a manner that the passage opening 17 is arranged in the bypass channel 10. Consequently, the bypass channel 10 is opened for exhaust gas to flow through.
  • the flow cross-section between two adjacent guide blades 12 is maximal. If the guide blades 12 are moved away out of the first position through rotation about their centre longitudinal axis M, the movement of the face plate 16 implies a movement of the passage opening 17 provided thereon out of the bypass channel 10, so that the latter is now closed off by the face plate 16 in a fluid-tight manner.
  • Figures 3 and 4 which correspond to the Figures 1 and 2 , i.e. Figure 3 shows the turbine 1 in a longitudinal section, Figure 4 the variable turbine geometry 11 in a top view.
  • the adjustment of the guide blade leaves 13, which is accompanied by the rotating of the guide blades 12 in the process brings about a reduction of the flow cross-section between two adjacent guide blades 12 in the conventional manner.
  • the third position of the guide blades 12 shown in the Figures 3 and 4 which corresponds to an intermediate position of the guide blades 12 between the first and the second position, in which the bypass channels 10 are just no longer opened, the flow cross-section between two adjacent guide blades 12 is reduced with respect to the first position.
  • a fastening ring 20 arranged concentrically to the turbine wheel 6 can be provided in the turbine housing 2.
  • the fastening ring 20 can have a recess 22 for each closure element 15, in particular for each face plate 16.
  • each recess 22 is formed complementarily to the closure element 15 or to the face plate 16, in which the closure element 10 or the face plate 16 is at least partially received.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP14165847.6A 2014-04-24 2014-04-24 Turbine à géométrie variable avec canal de dérivation pour turbocompresseur à gaz d'échappement Withdrawn EP2937521A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14165847.6A EP2937521A1 (fr) 2014-04-24 2014-04-24 Turbine à géométrie variable avec canal de dérivation pour turbocompresseur à gaz d'échappement

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14165847.6A EP2937521A1 (fr) 2014-04-24 2014-04-24 Turbine à géométrie variable avec canal de dérivation pour turbocompresseur à gaz d'échappement

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Publication Number Publication Date
EP2937521A1 true EP2937521A1 (fr) 2015-10-28

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EP14165847.6A Withdrawn EP2937521A1 (fr) 2014-04-24 2014-04-24 Turbine à géométrie variable avec canal de dérivation pour turbocompresseur à gaz d'échappement

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110439675A (zh) * 2018-05-04 2019-11-12 现代自动车株式会社 用于车辆的可变几何涡轮增压器
EP3705688A1 (fr) * 2019-03-07 2020-09-09 BorgWarner Inc. Agencement de turbine à géométrie variable

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3645645A (en) * 1970-10-19 1972-02-29 Garrett Corp Variable-area nozzle seal
EP0433560A1 (fr) * 1989-12-18 1991-06-26 Dr.Ing.h.c. F. Porsche Aktiengesellschaft Turbochargeur à gaz pour un moteur à combustion interne
US20030014972A1 (en) * 2001-01-16 2003-01-23 Arnold Steven Don Variable geometry turbocharger having internal bypass exhaust gas flow
EP1433937A1 (fr) * 2002-12-23 2004-06-30 BorgWarner Inc. Turbocompresseur avec la dérivation integrée dans le carter et méthode de fabrication
US7533641B1 (en) * 2006-04-17 2009-05-19 Jason Stewart Jackson Poppet valve and engine using same
DE102011120880A1 (de) * 2011-12-09 2013-06-13 Ihi Charging Systems International Gmbh Turbine für einen Abgasturbolader
DE102012202907A1 (de) * 2012-02-27 2013-08-29 Continental Automotive Gmbh Abgasturbolader mit relativ zueinander verdrehbaren Leitgitterringen

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3645645A (en) * 1970-10-19 1972-02-29 Garrett Corp Variable-area nozzle seal
EP0433560A1 (fr) * 1989-12-18 1991-06-26 Dr.Ing.h.c. F. Porsche Aktiengesellschaft Turbochargeur à gaz pour un moteur à combustion interne
US20030014972A1 (en) * 2001-01-16 2003-01-23 Arnold Steven Don Variable geometry turbocharger having internal bypass exhaust gas flow
EP1433937A1 (fr) * 2002-12-23 2004-06-30 BorgWarner Inc. Turbocompresseur avec la dérivation integrée dans le carter et méthode de fabrication
US7533641B1 (en) * 2006-04-17 2009-05-19 Jason Stewart Jackson Poppet valve and engine using same
DE102011120880A1 (de) * 2011-12-09 2013-06-13 Ihi Charging Systems International Gmbh Turbine für einen Abgasturbolader
DE102012202907A1 (de) * 2012-02-27 2013-08-29 Continental Automotive Gmbh Abgasturbolader mit relativ zueinander verdrehbaren Leitgitterringen

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110439675A (zh) * 2018-05-04 2019-11-12 现代自动车株式会社 用于车辆的可变几何涡轮增压器
KR20190127295A (ko) 2018-05-04 2019-11-13 현대자동차주식회사 차량용 vgt
US10508592B2 (en) 2018-05-04 2019-12-17 Hyundai Motor Company VGT for vehicle
CN110439675B (zh) * 2018-05-04 2022-06-14 现代自动车株式会社 用于车辆的可变几何涡轮增压器
DE102018217856B4 (de) 2018-05-04 2023-12-07 Hyundai Motor Company VTG-Lader für Fahrzeug
EP3705688A1 (fr) * 2019-03-07 2020-09-09 BorgWarner Inc. Agencement de turbine à géométrie variable

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