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WO2009106166A1 - Carter de turbine refroidi à double paroi - Google Patents

Carter de turbine refroidi à double paroi Download PDF

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Publication number
WO2009106166A1
WO2009106166A1 PCT/EP2008/065743 EP2008065743W WO2009106166A1 WO 2009106166 A1 WO2009106166 A1 WO 2009106166A1 EP 2008065743 W EP2008065743 W EP 2008065743W WO 2009106166 A1 WO2009106166 A1 WO 2009106166A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine housing
double
walled
coolant
housing according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/EP2008/065743
Other languages
German (de)
English (en)
Inventor
Ralf Böning
Hartmut Claus
Robert Vetter
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.)
Continental Automotive GmbH
Original Assignee
Continental Automotive GmbH
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 Continental Automotive GmbH filed Critical Continental Automotive GmbH
Publication of WO2009106166A1 publication Critical patent/WO2009106166A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
    • F02B37/183—Arrangements of bypass valves or actuators therefor
    • 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
    • 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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the invention relates to a cooled turbine housing of a turbocharger and a turbocharger with such a turbine housing.
  • turbochargers have an exhaust gas turbine, which is arranged in an exhaust gas flow and is connected via a turbo shaft to a compressor in the intake tract.
  • the exhaust flow directed through an exhaust manifold into the turbine housing of the turbine drives its turbine wheel.
  • the turbine wheel drives the compressor wheel, whereby the compressor increases the pressure in the intake tract of the engine, so that during the intake stroke, a larger amount of air enters the cylinder. This means that more oxygen is available and a correspondingly larger amount of fuel can be burned. This can increase the power output of the motor.
  • the components Due to the high exhaust gas temperatures of the turbocharger, the components, in particular the turbine housing, are subjected to high thermal loads. In passenger car gasoline engines, the exhaust gas temperatures may be up to 1100 ° C, for example. This can lead to a significant temperature load of turbocharger components, for example, in full-load or full-load operation.
  • the materials for the housing parts of the turbine are designed from a strength point of view at high temperatures.
  • Highly heat-resistant materials are used, which generally have high proportions of very expensive alloying elements.
  • the use of such materials has a significant impact on the price of a turbocharger.
  • the alloying element used is mainly nickel. Due to the high nickel content of the material, cast materials can withstand the high temperatures. Nickel is but a relatively expensive material and is also subject to strong world market fluctuations.
  • a turbocharger with a multi-walled outer housing.
  • the outer housing consists of several shells, as well as a welded-in water inlet and a water drain.
  • a sliding seat is arranged in the region of an inlet funnel between the inlet funnel and the outer shells, which enables the thermally induced length compensation between the sheet metal parts.
  • a wire cushion stabilizes the sliding seat.
  • the turbocharger has the disadvantage that the turbocharger housing has a complicated structure.
  • the turbocharger housing is composed of three walls, wherein the two outer walls form a cavity through which cooling water is introduced.
  • the inner wall and the middle wall also form a cavity which serves as an air gap insulation.
  • a turbine housing for a turbocharger in particular for a
  • the present invention provides a double-walled turbine housing for a turbocharger: wherein the turbine housing forms a first wall and at least one shell member is externally attached to the turbine housing and forms a second wall, both walls forming a cavity into which a coolant is insertable.
  • the double-walled, cooled turbine housing has the advantage that it is simple and inexpensive to manufacture, in contrast to the three-walled turbine housing, according to the prior art. This must be welded together from three layers of sheet metal, whereby the sheet metal layers must be suitably formed in advance in order to form cavities.
  • a first cavity forms an air gap insulation, which is formed from the inner and middle sheet-metal wall.
  • the middle and outer metal wall in turn form a cavity through which cooling liquid flows.
  • the turbine housing is, for example, a cast part, for example an aluminum cast part, a cast iron part or a cast steel part.
  • the cooling device also makes it possible to use those less heat-resistant materials.
  • the respective shell element is a cast part, for example an aluminum cast part, a cast iron part and / or a cast steel part.
  • the shell element can be formed here as a diecast part. This has the advantage that In particular, more complex forms can be produced, which can not otherwise be readily prepared by forming.
  • the shell element is for example a sheet metal part.
  • Sheet has the advantage that it is inexpensive.
  • the shell element has, for example, at least one first connection for introducing a coolant and / or at least one second connection for discharging the coolant.
  • first connection for introducing a coolant
  • second connection for discharging the coolant.
  • shell elements can be provided underneath without such connections.
  • the inlet and outlet ports have the advantage that the turbine housing flows around with fresh coolant and the heated, used coolant can be removed and replaced with fresh coolant.
  • first and second connections are arranged adjacent to one another or on the same side on the turbine housing, wherein optionally additionally a partition wall element between the two connections can be arranged north.
  • the partition element has the advantage that it substantially prevents a cooling medium flowing in through the first connection from being able to flow out again immediately via the second connection before cooling the turbine housing.
  • the first and second connections on the turbine housing or the shell element (s) are arranged apart from one another, for example substantially opposite one another.
  • the shell element can be fastened to the turbine housing, for example by means of welding, soldering, screwing and / or gluing, wherein the turbine housing optionally has corresponding fastening sections for receiving the shell element.
  • the attachment portions have the advantage of simplifying placement and attachment of the shell members to the turbine housing.
  • a liquid or gaseous coolant is used as the coolant.
  • a coolant in this case for example, cooling water can be used.
  • the cooling water may, for example, be diverted from an engine connected to a turbocharger of the turbine housing. This has the advantage that no separate cooling circuit has to be provided. Furthermore, it is also possible to return the used cooling water to the cooling circuit of the engine.
  • At least one or more flow elements are arranged in the cavity.
  • the respective flow element can be formed on the turbine housing or the shell element. This has the advantage that the flow elements additionally conduct the coolant flow.
  • At least two and more shell members form the second wall to provide the cavity with the turbine housing.
  • at least two and more shell members form the second wall to provide the cavity with the turbine housing.
  • a plurality of sheet metal parts can be very easily assembled as shell elements to form an outer second wall and connected to one another.
  • the shell member is attached to the turbine housing liquid-tight or gas-tight.
  • the shell elements can be connected, for example gas-tight with the turbine housing. But it is also possible that even in such a case, a liquid-tight connection is sufficient because coolant in the form of water vapor can escape to a limited extent to the outside, without being a relevant problem.
  • the plastic or the fiber composite material are chosen so that they are suitable for the temperatures that occur in this area, i. E. the temperatures that a turbocharger turbine housing normally has to withstand or the temperatures that a shell element of the cooling jacket must absorb. That The plastic or fiber composite material must be suitably heat-resistant or heat-resistant.
  • Fig. 1 is a perspective view of one by means of a
  • Fig. 2 is a sectional view B-B through the cooled
  • Turbine housing according to FIG. 1;
  • FIG. 3 is a perspective view of the cooled turbine housing of FIG. 1, with the side of the
  • Turbine housing is shown with its two terminals; and 4 shows a sectional view of a turbine housing cooled by means of a coolant according to a second embodiment of the invention.
  • the invention is essentially directed to reducing the thermal load of the turbocharger by cooling its turbine housing.
  • the cooling water jacket is poured into the turbine housing or a pure sheet metal housing is provided, attached to a turbine housing a coolant jacket.
  • the coolant jacket consisting of one or more shell elements, attached to the outside of the turbine housing to form a cavity with this in which a coolant can be introduced.
  • the shell element or the shell elements for forming the cooling jacket can in this case for example by means of welding and / or soldering, etc. are attached.
  • the respective shell element may consist of a sheet metal, for example of steel or an aluminum alloy, for example, in a turbine housing, which is welded or soldered to the turbine housing, for example.
  • a shell element made of sheet metal in this case, for example, have a sheet thickness of 0.8mm to 2mm. Basically, the sheet thickness is not limited to this area, but may also have a smaller or larger sheet thicknesses, depending on the function and purpose.
  • the respective shell elements may be made of a die-cast part which can be welded or soldered to the aluminum alloy, for example.
  • the die-cast part has, for example, a thickness in a range of 2 mm to 3 mm or 2.5 mm to 3 mm on. Basically, the thickness of the die-cast part is not limited to this area, but may also have a smaller or larger thickness, depending on the function and use purpose.
  • the cooling jacket of the at least one shell element is welded to the turbine housing in a liquid-tight or gas-tight manner in order to form a suitable cavity for the cooling medium.
  • the aim of the invention is to reduce the component temperature of the turbine housing in order to allow the use of cheaper materials for the turbine housing. So that, for example, the use of expensive alloying elements, such as nickel, essentially dispensed with or at least reduced its share. This is achieved by, as described above, around the actual turbine housing part a cooling jacket consisting of one or more
  • Shell elements for example, welded and / or soldered.
  • a cavity is formed between the respective shell element and the turbine housing, into which a coolant can be introduced in order to cool the turbine housing.
  • a coolant can be introduced in order to cool the turbine housing. It is also conceivable, not only to use the cooling jacket exclusively for cooling, but also to heat, for example, the turbine housing by already heated by the engine cooling water is used.
  • a turbine housing 10 which can be cooled by means of a coolant.
  • the turbine housing 10 itself is in this case for example a cast part, for example made of an aluminum alloy or another suitable material or material combination.
  • one or more shell elements 14, 16 are provided to form a cavity 12 about the turbine housing 10.
  • the cooling jacket 18 is included in For example, formed from a first and second shell member 14, 16.
  • the respective shell element 14, 16 can, as described above, for example, consist of a metal sheet.
  • the sheet is shaped accordingly to form the contour of the cooling jacket 18.
  • the shell elements 14, 16 are fastened to the turbine housing 10.
  • at least one connection 20 for an inlet and a connection for an outlet 22 of the coolant are provided on the cooling jacket 18.
  • One or both ports 20, 22 may be formed on the corresponding shell element 14, 16 or attached thereto as a separate part.
  • a corresponding pressure cast part can also be provided. This is chosen in its material so that it can be suitably fixed to the turbine housing 10, i. that it can be suitably welded and / or soldered to the turbine housing 10, for example. The same applies to the sheet metal parts.
  • the two shell elements 14, 16 are fastened, for example, to corresponding attachment sections 24 of the turbine housing 10 and further connected to each other at their ends 26, for example also by welding and / or soldering.
  • At least one, two or more flow elements 28 may be provided inside the cooling jacket 18 for conducting, for example, a liquid coolant.
  • the flow element 28 may be formed, for example, in the form of a rib which extends in the radial direction, as indicated in FIG. 1 in a greatly simplified manner with a dashed line. It is also possible to provide a plurality of such flow ribs 28 spaced from one another, for example two and more. In principle, other shapes and arrangements of flow elements 28 may be provided.
  • the flow elements 28 can be formed on the turbine housing 10, or can be formed there, for example, with are formed or attached thereto, and / or provided on the inside of the corresponding shell member 14, 16 or attached thereto or molded.
  • cooling water As coolant, which is introduced into the cooling jacket 18 via the first connection 20 or inlet connection, cooling water can be used, for example, or another suitable coolant. Furthermore, cooling water from the engine can be used or diverted from the engine as cooling water, for example, or cooling water can be provided in a separate circuit.
  • the coolant is supplied via the first connection 20 to the cooling jacket of the turbine housing 10.
  • the two terminals 20, 22 may, as shown in Fig. 1, for example, be arranged on the same side or directly adjacent to each other or in the vicinity, wherein the two terminals 20, 22 are separated from each other, for example, by a partition wall element 30 ,
  • the partition wall element 30 is positioned in the cooling jacket 18 of the turbine housing 10 in such a way that the coolant essentially flows first into the cooling jacket 18 or its cavity 12 via the first connection 20 and does not flow off again immediately via the adjacent second connection 22, but instead first the turbine housing 10 flows against or at least partially or substantially flows around.
  • FIG. 2 shows the cooled turbine housing 10 according to FIG. 1 in a sectional view BB.
  • the two shell elements 14, 16 are shown.
  • a device for actuating a bypass channel 32 is provided on the turbine housing 10, for example.
  • This also has, for example, a fastening section 24 into which the respective shell element 14, 16 is inserted and fastened.
  • the cooling jacket 18 according to the invention is independent of such a device for actuating a bypass channel 32.
  • any type of turbocharger with turbine housing 10 can be used.
  • the attachment portions 24 on the turbine housing 10 are provided, for example, in the form of a recess 34 in Fig. 1 into which the respective shell member 14, 16 is inserted and connected to the turbine housing 10, e.g. welded and / or soldered.
  • the recess 34 may be formed in the form of a groove or a slot, in which the shell member 14, 16 inserted and, for example, welded.
  • the respective fastening portions 24 on the turbine housing 10 may be the same or different, depending on the function and purpose. This applies to all embodiments according to the invention.
  • the flow element 28 is shown in FIG. 2 with a dashed line. The provision of flow elements is an optional feature. This also applies to all embodiments of the invention.
  • FIG. 3 the turbine housing 10 according to FIGS. 1 and 2 from the side of the two terminals 20, 22 is shown.
  • the partition wall element 30 between the two terminals 20, 22 is shown.
  • the partition wall element 30 is in this case on the Turbine housing 10 integrally formed.
  • the two shell elements 14, 16 are fastened, for example, directly to the partition wall element 30.
  • the partition wall element 30 each have a fastening portion 24, for example in the form of a depression or step.
  • the inlet port 20 is provided on the first shell member 14 and the outlet port 22 on the second shell member 16, as shown in Fig. 1.
  • the two connections 20, 22 are, for example, separately attached to the respective shell element 14, 16 or formed on or molded onto it and, as shown in FIGS. 1 and 3, for example provided with an additional connection element 36 or a connection cap ,
  • the two terminals 20, 22 apart as far as possible by the terminals 20, 22 are arranged, for example, substantially opposite one another, as indicated in the schematic representation in Fig. 4 with a dashed line.
  • the coolant first flows through the first connection 20 into the cooling jacket 18 or the cavity 12 formed by it.
  • the coolant flows on both sides around the turbine housing 10 and at the end via the second connection 22 again out of the cooling jacket 18 or the cavity 12 out, as indicated by the arrows in Fig. 4.
  • the terminals 20, 22 can be provided at the same height or different heights. Furthermore, at least one, two or more inlet connections 20 and / or outlet connections 22 can be provided, wherein the connections 20, 22 can be positioned as desired, preferably in such a way that the coolant forms the turbine housing 10 Cool flow suitably and can flow out of the cooling jacket 18 again. This applies to all embodiments of the invention.
  • the advantage of the above-described embodiment according to the invention, in particular compared to an embodiment with a cast-in cooling jacket, is that the cooling jacket 18 can be realized even with very small passenger car turbine housings 10 without generating disproportionate production costs.
  • the coolant such as cooling water
  • the coolant may, as described above, be taken from a cooling circuit of an engine connected to the turbocharger.
  • the cooling circuit is formed for example of an engine block, a thermostat, a radiator and a coolant pump. After the cooling of the turbine housing 10, the coolant can be returned to the cooling circuit.
  • the invention is not limited to this embodiment of a refrigeration cycle.
  • the cooling jacket 18 for cooling the turbine housing 10 this can also be made of less heat-resistant materials.
  • the respective housing 10 may include materials such as aluminum, low alloy steels, gray cast iron, etc. Therefore, for example, can be dispensed with the use of expensive alloying elements such as nickel or its share is at least reduced. This further has the advantage that manufacturing costs can be reduced.
  • the design of the turbine housing 10 and / or the respective shell element 14, 16 not only in iron or non-ferrous metals but also in plastic and / or fiber composites. The plastics or fiber composites are chosen so that they are suitable for the respective resulting temperatures of the turbine housing 10 formed therefrom and / or shell element 14, 16.
  • the turbine housing 10 and the respective shell element 14, 16 are connected accordingly, for example by welding, soldering, screwing with a seal between the respective shell element 14, 16 and turbine housing 10 and / or gluing, to name just a few attachment methods.

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

Abstract

L'invention concerne un carter de turbine (10), à double paroi, pour un turbocompresseur, formant une première et une deuxième paroi. Au moins un élément coque (14, 16) est fixé à l'extérieur sur le carter de turbine (10). Les deux parois forment une cavité (12) dans laquelle peut être introduit un fluide de refroidissement.
PCT/EP2008/065743 2008-02-27 2008-11-18 Carter de turbine refroidi à double paroi Ceased WO2009106166A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008011257A DE102008011257A1 (de) 2008-02-27 2008-02-27 Gekühltes Turbinengehäuse
DE102008011257.7 2008-02-27

Publications (1)

Publication Number Publication Date
WO2009106166A1 true WO2009106166A1 (fr) 2009-09-03

Family

ID=40622145

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/065743 Ceased WO2009106166A1 (fr) 2008-02-27 2008-11-18 Carter de turbine refroidi à double paroi

Country Status (2)

Country Link
DE (1) DE102008011257A1 (fr)
WO (1) WO2009106166A1 (fr)

Cited By (11)

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WO2011053513A3 (fr) * 2009-10-30 2011-09-22 Borgwarner Inc. Corps de turbine d'un turbocompresseur de gaz d'échappement
US20110296834A1 (en) * 2010-06-07 2011-12-08 Ford Global Technologies, Llc Separately cooled turbocharger for maintaining a no-flow strategy of an engine block coolant jacket
WO2012072672A1 (fr) * 2010-12-03 2012-06-07 Continental Automotive Gmbh Turbocompresseur à gaz d'échappement comprenant une soupape de dérivation
EP2299087A3 (fr) * 2009-09-22 2012-11-07 Benteler Automobiltechnik GmbH Turbocompresseur
CN103348116A (zh) * 2011-02-10 2013-10-09 大陆汽车有限公司 具有冷却的涡轮机壳体和减小的压力损失的废气涡轮增压器
CN104271287A (zh) * 2012-04-27 2015-01-07 大丰工业株式会社 涡轮增压器的轴承套的制造方法以及涡轮增压器的轴承套
JP2016098671A (ja) * 2014-11-19 2016-05-30 アイシン高丘株式会社 タービンハウジング
JP2016098672A (ja) * 2014-11-19 2016-05-30 アイシン高丘株式会社 タービンハウジング
US9945258B2 (en) 2014-10-10 2018-04-17 Ford Global Technologies, Llc Sheet metal turbine housing with cellular structure reinforcement
US10273866B2 (en) 2014-09-16 2019-04-30 Ford Global Technologies, Llc Supercharged internal combustion engine with turbine which can be liquid-cooled, and method for controlling the cooling of said turbine
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US9518479B2 (en) 2011-03-14 2016-12-13 Borgwarner Inc. Turbine housing of an exhaust turbocharger
EP2554820B1 (fr) 2011-08-03 2016-12-14 Ford Global Technologies, LLC Moteur à combustion interne chargé doté de deux turbines et procédé de fonctionnement d'un tel moteur à combustion interne
EP2557292A1 (fr) 2011-08-10 2013-02-13 Ford Global Technologies, LLC Moteur à combustion interne refroidi par liquide doté d'un système de turbocompression à gaz d'échappement
US9011086B2 (en) * 2011-12-07 2015-04-21 Honeywell International Inc. Treated valve seat
DE102012100646B4 (de) 2012-01-26 2017-03-16 Saxess Holding Gmbh Turbinen- und Generatorgehäuse
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DE102014201732B4 (de) 2013-02-28 2024-03-28 Ford Global Technologies, Llc Brennkraftmaschine mit flüssigkeitsgekühlter Turbine
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DE202013100884U1 (de) 2013-02-28 2013-03-21 Ford Global Technologies, Llc. Flüssigkeitsgekühlte Turbine mit Lagergehäuse
DE102013206245A1 (de) 2013-04-09 2014-10-09 Ford Global Technologies, Llc Flüssigkeitsgekühlte Turbine
DE202013101510U1 (de) 2013-04-09 2013-04-19 Ford Global Technologies, Llc. Flüssigkeitsgekühlte Turbine
DE102013216112A1 (de) 2013-08-14 2015-02-19 Ford Global Technologies, Llc Zylinderkopf mit einer Axialturbine
DE202013103704U1 (de) 2013-08-14 2013-08-27 Ford Global Technologies, Llc Zylinderkopf mit einer Axialturbine
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