EP1747350A1 - Turbocompresseur possedant une inertie thermique limitee et son procede de fabrication - Google Patents

Turbocompresseur possedant une inertie thermique limitee et son procede de fabrication

Info

Publication number
EP1747350A1
EP1747350A1 EP04732320A EP04732320A EP1747350A1 EP 1747350 A1 EP1747350 A1 EP 1747350A1 EP 04732320 A EP04732320 A EP 04732320A EP 04732320 A EP04732320 A EP 04732320A EP 1747350 A1 EP1747350 A1 EP 1747350A1
Authority
EP
European Patent Office
Prior art keywords
turbine housing
housing unit
pieces
turbine
volute
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Withdrawn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
EP04732320A
Other languages
German (de)
English (en)
Inventor
Edouard Honeywell Garrett SA MASSART
Marylène Honeywell Garrett SA RUFFINONI
Michel Honeywell Garrett SA MILLOT
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.)
Honeywell International Inc
Original Assignee
Honeywell International Inc
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 Honeywell International Inc filed Critical Honeywell International Inc
Publication of EP1747350A1 publication Critical patent/EP1747350A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • 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
    • F01D25/145—Thermally insulated 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics

Definitions

  • turbocharger having a reduced thermal inertia and a method of producing the same.
  • turbochargers consist of three principle components: a turbine, a compressor, and a housing unit. In operation, the turbine captures high-temperature gases coming from the engine exhaust manifold. These exhaust gases then are used to drive a compressor which, in term, pumps high pressure air into the engine inlet and combustion chambers.
  • turbocharger turbine housing units and gas exhaust manifolds for gasoline and diesel engines are typically made of steel or cast iron. Steel and iron inherently possess a high thermal inertia, i.e. a high ability of conducting and storing heat. As a result, the captured gas heat energy dissipates and less energy is available to drive the turbocharger turbine, thereby reducing the performance and efficiency of the turbine.
  • the turbine housing unit it takes considerable time for the turbine housing unit to match the temperature of the captured gas when there is a substantial change of exhaust gas temperature.
  • the heat energy loss may delay the activation of an exhaust gas catalytic converter disposed downstream of the turbocharger turbine in the exhaust line of the internal combustion engine at a cold start of the engine.
  • the delay of the full operation of the exhaust gas catalytic converter increases the emission levels as monitored at the exhaust tail pipe.
  • One method to minimize this emission is through reducing the thermal inertia of the turbine housing unit.
  • One approach to reducing the thermal inertia of the turbine housing unit is to replace the steel or iron material of the turbine housing unit with a material having a low thermal inertia such as a carbon-carbon composite material as disclosed in US 5 810 556 A.
  • a thermal insulating layer such as a ceramic layer on the inner wall surfaces of the turbine housing unit.
  • the thermal insulating layer has to be rather thin to compensate for the vibrations and shock in operation, thereby reducing the thermal inertia of the turbine housing unit only to a small extent. If, on the other hand, the thermal insulating layer is made thicker to reduce the thermal inertia of the turbine housing unit to the full extent, thermal stress at the interface between the thermal insulating layer and the metallic material of the turbine housing unit becomes excessively high, so that the thermal insulating layer is likely to come off or spall.
  • the above problem is alleviated to a large extent by dividing the turbine housing unit into a plurality of separate turbine housing pieces, each turbine housing piece having an inner wall surface that defines a part of the internal passage of the finished turbine housing unit. It is easier to apply the thermal insulating layer to the inner wall surfaces of the individual turbine housing pieces than to the inner wall surfaces of a finished turbine housing unit. For example, it is difficult to deposit a thermal insulating material on the inside of an internal passage having a scroll configuration such as the volute for receiving the turbine wheel. Even if one succeeded in depositing the thermal insulating material with a sufficient thickness, thickness and bonding strength of the thermal insulating layer would certainly differ depending on the accessibility of the respective location of deposition.
  • the above problem is solved by providing a method of producing a turbine housing unit for a turbocharger of an internal combustion engine, said turbine housing unit having an internal passage comprising an inlet and an outlet and a volute for receiving a turbine wheel, said method comprising: preparing a plurality of metallic turbine housing pieces, each turbine housing piece having an inner wall surface that defines a part of said internal passage; applying a thermal insulating layer on said inner wall surfaces; and joining the turbine housing pieces at respective parting lines after applying the thermal insulating layer to obtain an integral turbine housing unit.
  • thermal insulating layer When applying the thermal insulating layer on the inner wall surfaces of the individual turbine housing pieces, it is possible to further optimize the process parameters as compared with the case of applying a thermal insulating layer to the inner wall surfaces of a finished turbine housing unit. As result, a thermal insulating layer having a greater and/or more controlled thickness and/or a higher bonding strength can be achieved.
  • a turbine housing unit for a turbocharger of an internal combustion engine having an internal passage comprising an inlet and an outlet and a volute for receiving a turbine wheel
  • said turbine housing unit further comprising: a plurality of metallic turbine housing pieces, each turbine housing piece having an inner wall surface that defines a part of said internal passage, and said turbine housing pieces being joined at respective parting lines; and a thermal insulating layer on said inner wall surfaces.
  • the above turbine housing unit is readily discernible from a conventional turbine housing unit having a one-piece configuration in that it has a multiple-piece configuration with the individual pieces being joined at the parting lines.
  • the thermal insulating layer may have a greater and/or more controlled thickness and/or a higher bonding strength.
  • the plurality of turbine housing pieces includes two turbine housing pieces that are joined at a parting line which divides the volute in an axial direction of the volute. In this case it is easier to apply the thermal insulating layer on the inner surface walls of the volute, which has a complicated scroll configuration.
  • the internal passage of the turbine housing unit there may be provided a waste gate for bypassing the turbine wheel to be received in the volute and for waste-gating excess exhaust gas to the exhaust gas system downstream of the turbocharger.
  • the turbine housing pieces are prepared by casting.
  • each turbine housing piece can be cast separately, or the turbine housing pieces are prepared by casting a one-piece turbine housing and then cutting the turbine housing into pieces.
  • the turbine housing pieces are preferably made of steel or iron.
  • the thermal insulating layer is preferably a thermal barrier coating including a ceramic top layer and a metallic bond coat.
  • a ceramic top layer of stabilized zirconia and an MCrAlY bond coat (where M is selected from a group of cobalt, nickel, and iron) may be used.
  • thermal barrier coatings have a high spalling resistance and are known as protective coatings which insulate the blades and vanes of aircraft engines or gas turbine engines (see, for example, US 6 395 343 Bl) .
  • the bond coat and the ceramic top layer are preferably applied by plasma spraying. As explained above, it is difficult to deposit a material on the inside of an internal passage having a complicated and long configuration such as the volute. This is all the more true for plasma spraying.
  • the metallic bond coat and the ceramic top layer exhibit a sufficient bonding strength only if, in the plasma spraying process, the molten particles have an appropriate temperature when they reach the location of impact, and if the molten particles have an angle of impact that is not excessively acute.
  • FIG. 1 is a cross-sectional view of a turbine housing unit having a two-piece configuration according to one embodiment of the invention
  • FIGS. 2 and 3 are perspective views of the turbine housing pieces shown in FIG. 1
  • FIGS. 4 and 5 are perspective views of a turbine housing unit having a three-piece configuration according to another embodiment of the invention.
  • FIG. 1 there is provided a two-piece turbine housing unit for a turbocharger of an internal combustion engine.
  • the turbine housing unit has an internal passage comprising an inlet 10, an outlet 14, and a volute 12 having a single scroll configuration for receiving a turbine wheel. If installed in an exhaust system of an internal combustion engine, the internal passage guides exhaust gas discharged from the internal combustion engine from the inlet 10 to the turbine wheel in the volute 12 prior to discharge through the outlet 14.
  • the internal passage further comprises a waste gate 16 at the inlet 10 which communicates the inlet 10 with the outlet 14 to bypass the turbine wheel and to waste- gate excess exhaust gas to the outlet 14.
  • the turbine housing unit is constituted of first and second turbine housing pieces 2 and 4 which are welded at a parting line 6 which divides the volute 12 into two parts in an axial direction of the volute 12.
  • the first turbine housing piece 2 defines half of the inlet 10 and the volute 12, the main part of the waste gate 16, and the outlet 14.
  • the second turbine housing piece 4 defines the other half of the inlet 10 and the volute 12, and a part of the waste gate 16 that opens to the inlet 10.
  • the inner wall surfaces of the outlet 14 and the volute 12 are covered with a thermal insulating layer.
  • the inner wall surfaces of the inlet 10 and the waste gate 16 are covered by the thermal insulating layer 8 as well.
  • the turbine housing pieces 2, 4 are made of cast iron.
  • HK30 can be used, a Fe-Cr-Ni alloy consisting of 0.25-0.35 wt% C, 0.75-1.75 wt% Si, 23-27 wt% Cr, 19-22 wt% Ni, 1.2-1.5 wt% Nb, balance Fe and unavoidable impurities such as Mn, P, S, Mo.
  • the thermal insulating layer 8 is a plasma-sprayed thermal barrier coating including a ceramic top layer of yttria stabilized zirconia and an MCrAlY bond coat.
  • the powder Metco 204C-NSTM may be used, containing 8% Y 2 0 3 , balance Zr0 2 and having spheroidal particles with a size of -125 +46 ⁇ m.
  • the NiCrAlY powder Amdry 962TM may be used, containing 22% Ni, 10% Cr, 1% Al and less than 1% Y and having spheroidal particles with a size- of -106 +56 ⁇ m.
  • the thickness of the bond coat is 50 to 150 ⁇ m, while the thickness of the ceramic layer may vary in the 100 to 500 ⁇ m range.
  • the ceramic top has an interconnected network of subcritical microcracks with micron-width opening displacements, which reduce the effective modulus (increase compliance) of the stabilized zirconia layer in the plane of the coating.
  • Increased compliance provided by the microcracks enhances coating durability by eliminating or minimizing stresses associated with thermal gradient and cast iron/zirconia thermal expansion mismatch strains in the stabilized zirconia layer.
  • the ceramic top layer has a bond strength as high as 50 MPa which is considered to be robust in the operation of a turbocharger.
  • the turbine housing unit according to the above embodiment is prepared as follows. First, the two turbine housing pieces 2, 4 are prepared separately by casting iron. The cast pieces are heat-treated, machined at the connections formed on the inlet 10 and the outlet 16 and at the parting line 6, and finally washed to obtain the first and second turbine housing pieces 2, 4 shown in FIGS. 2 and 3, respectively. Before coating, the machined surfaces of the first and second turbine housing pieces 2, 4 are masked with high temperature tapes or a specific tool. First, the bond coat is applied to the inner wall surfaces that define the respective parts of the internal passage by plasma-spraying NiCrAlY particles. Then, the bond coat is heat-treated to create a chemical bonding between the bond coat and the substrate material.
  • yttria stabilized zirconia particles are applied to the bond coat by plasma-spraying to form the ceramic top layer with the above-mentioned interconnected network of subcritical microcracks.
  • the plasma-spraying is performed in the direction indicated by the hatched arrows in FIGS. 2 and 3.
  • the bond coat and the ceramic top layer may be sprayed from only one side (i.e. from the side facing the inner wall surfaces of the inlet 10, the volute and the opening of the waste gate 16)
  • the bond coat and the ceramic top layer are preferably sprayed from two sides (i.e.
  • the turbine housing pieces are configured such that there is sufficient access to the inner wall surfaces for the plasma-spray gun to cover the entire internal passage with the bond coat and the ceramic top layer.
  • the coated turbine housing pieces 2, 4 are joined at the parting line 6, for example, by automatic laser welding.
  • the ceramic top layer is sufficiently crack resistant for withstanding the welding process without damage.
  • the above method of producing the turbine housing unit has the advantage that there is good access to the inner wall surfaces that define the internal passage of the turbine housing unit. Thanks to the good accessibility, the process parameters for applying the bond coat and, above all, the ceramic top layer can be optimized to achieve a thermal barrier coating having a sufficient thickness and a good bonding strength. Further, since the entire inner wall surface of the internal passage is coated with the thermal insulating ceramic layer, the thermal inertia of the turbine housing unit can be reduced to a large extent, thus increasing the performance and efficiency of the turbocharger and accelerating the activation of an exhaust gas catalytic converter disposed downstream of the turbocharger at a cold start of the internal combustion engine.
  • the above embodiment can be modified as shown in FIGS. 4 and 5.
  • FIGS. 4 and 5 show a perspective view of turbine housing pieces of a three-piece turbine housing unit according to another embodiment of the invention.
  • This embodiment differs from the one discussed above only in that the first turbine housing piece is sub-divided into two sub-pieces 2a, 2b along the longitudinal axis of the outlet 14.
  • Each sub-piece 2a, 2b defines a part of the inlet 10 and the volute 12, and one half of the waste gate 16.
  • Dividing the first turbine housing piece into the two sub-pieces 2a, 2b shown in FIGS. 4 and 5 improves the accessibility to the outlet 14 and the waste gate 16, so that the quality of the thermal insulating layer can be further improved.
  • the spraying direction is indicated by hatched arrows.
  • the turbine housing unit can be divided into four pieces or more, if need be.
  • the turbine housing unit may have an internal passage with a configuration different from the one shown in the drawings.
  • the waste port 16 can be omitted.
  • the volute 12 can have a twin scroll configuration to which sufficient access could be achieved by dividing the turbine housing unit at parting lines which run in the radial direction of each scroll.
  • the turbine housing pieces can be made of a metal other than cast iron, including steel.
  • the thermal insulating layer is not limited to a thermal barrier coating as described above. It is possible to use other bond coats and other ceramic top layers, or to apply the ceramic layer directly on the inner wall surfaces of the turbine housing pieces. Moreover, the thermal insulating layer need not be applied by plasma spraying. Other coating processes such as EB-PVD are appropriate as well. Besides, a thermal insulating material other than ceramic could be used, including glass and mineral. Still further, the risk of damage to the thermal insulating layer involved with the welding process can be reduced not only by masking the turbine housing pieces at the parting lines but also by selectively removing the applied thermal insulating layer in the vicinity of the edges of the turbine housing pieces at the parting lines before welding.
  • the machined surfaces of the parting lines can have a stepped configuration so as to make the welding stop in the turbine housing pieces before reaching the thermal insulating layer.
  • the turbine housing pieces can be joined by methods other than welding, including mechanical connections such as bolds, V-bands, a threaded connection, or the like.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Supercharger (AREA)

Abstract

L'invention concerne un carter de turbine de turbocompresseur de moteur à combustion interne possédant une inertie thermique limitée, ainsi que son procédé de fabrication. Ce carter de turbine comporte un passage intérieur composé d'une entrée (10), d'une sortie (14) et d'une volute (12) servant à recevoir une roue de turbine. Son procédé de fabrication consiste à: préparer une pluralité de pièces métalliques (2, 4) de carter de turbine, possédant chacune une surface de paroi intérieure définissant une partie du passage intérieur; appliquer une couche d'isolation thermique (8) sur les surfaces de la paroi intérieure et réunir ces pièces (2, 4) au niveau de lignes de séparation respectives (6) après application de la couche d'isolation thermique (8) afin d'obtenir un carter de turbine solidaire.
EP04732320A 2004-05-12 2004-05-12 Turbocompresseur possedant une inertie thermique limitee et son procede de fabrication Withdrawn EP1747350A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2004/005102 WO2005108747A1 (fr) 2004-05-12 2004-05-12 Turbocompresseur possedant une inertie thermique limitee et son procede de fabrication

Publications (1)

Publication Number Publication Date
EP1747350A1 true EP1747350A1 (fr) 2007-01-31

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Application Number Title Priority Date Filing Date
EP04732320A Withdrawn EP1747350A1 (fr) 2004-05-12 2004-05-12 Turbocompresseur possedant une inertie thermique limitee et son procede de fabrication

Country Status (2)

Country Link
EP (1) EP1747350A1 (fr)
WO (1) WO2005108747A1 (fr)

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EP1790832A1 (fr) * 2005-11-23 2007-05-30 ABB Turbo Systems AG Insulation pour un turbocompresseur
US9534576B2 (en) * 2011-12-30 2017-01-03 Xi'an Jiaotong University Cryogenic liquid turbine
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US10823061B2 (en) * 2016-07-15 2020-11-03 General Electric Company Engine air inlet having a double-panel heated wall

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