WO2008043539A1 - Compresseur pour un turbocompresseur à suralimentation et son procédé de refroidissement - Google Patents

Compresseur pour un turbocompresseur à suralimentation et son procédé de refroidissement Download PDF

Info

Publication number
WO2008043539A1
WO2008043539A1 PCT/EP2007/008804 EP2007008804W WO2008043539A1 WO 2008043539 A1 WO2008043539 A1 WO 2008043539A1 EP 2007008804 W EP2007008804 W EP 2007008804W WO 2008043539 A1 WO2008043539 A1 WO 2008043539A1
Authority
WO
WIPO (PCT)
Prior art keywords
compressor
wheel
cooling fluid
heat
cooling
Prior art date
Application number
PCT/EP2007/008804
Other languages
German (de)
English (en)
Inventor
Martin Meier
Ferdinand Werdecker
Herbert Mögele
Original Assignee
Man Diesel Se
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 Man Diesel Se filed Critical Man Diesel Se
Priority to CH00609/09A priority Critical patent/CH698234B1/de
Priority to JP2009531768A priority patent/JP2010506091A/ja
Publication of WO2008043539A1 publication Critical patent/WO2008043539A1/fr

Links

Classifications

    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/046—Heating, heat insulation or cooling means
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • 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
    • F05D2300/2112—Aluminium oxides
    • 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
    • F05D2300/2118—Zirconium oxides

Definitions

  • the present invention relates to a compressor for a turbocharger according to the preamble of claim 1 and a method for the cooling thereof.
  • a working medium in particular air
  • a compressor for combustion in an internal combustion engine This is coupled to a turbine, which in turn is driven by the exhaust gases of the internal combustion engine.
  • EP 0 518 026 A1 proposes an impingement air cooling of the compressor wheel rear side, in which cold air is introduced into a radial gap between the compressor wheel and the housing and acts there on the rear side of the compressor wheel.
  • WO 01/29426 A1 proposes indirect cooling, in which a cavity is provided in the part of the compressor section adjacent to the compressor wheel. is flowed through by a cooling fluid, so that heat from the compressor via a leakage flow in the radial gap and the part of the compressor housing in there. Cooling fluid is derived.
  • DE 20 2005 019 320 U 1 relates to the turbine acted upon by the hot exhaust gas, which is regularly exposed to higher temperatures than the compressor, and proposes to provide the blades with a thermal protection layer.
  • WO 01/29426 A1 it is therefore an object of the present invention to provide a compressor for a turbocharger in which, with a smaller amount of cooling fluid, the temperatures occurring during the compression of the working medium in the compressor wheel can be lowered.
  • a compressor according to the preamble of claim 1 is further developed by its characterizing feature. Claim 12 protects the method for cooling such a compressor.
  • a compressor for a turbocharger comprises a compressor wheel which is rotatably received in a compressor housing. It is preferably a radial compressor in which the axially sucked working medium is accelerated radially outwards by blades of the compressor wheel and then its velocity is converted into pressure.
  • a diffuser may be provided.
  • the rear side of the compressor wheel cools directly or indirectly by absorbing heat from it.
  • the compressor wheel is additionally provided at least partially with a heat input reducing coating.
  • the heat input from the compressed and thus heated working fluid can be reduced in the compressor so far that even a smaller amount of cooling fluid is sufficient to dissipate so much heat that the temperatures occurring in the Verdienterrad not exceed a maximum allowable value ü.
  • Lower amounts of cooling fluid advantageously only require fluid passages with smaller diameters and / or lower flow velocities.
  • a compressor according to the invention can build smaller, since supply and discharge lines and cooling fluid passages can be made smaller in the compressor housing.
  • the total amount of circulating cooling fluid can be reduced, allowing for a smaller cooling fluid reservoir.
  • a heat exchanger in which the cooling fluid discharges the heat to be removed from the compressor back to the environment can also be reduced.
  • a lower volume flow requires only a lower power to circulate the cooling fluid and thus increases the efficiency of a motor equipped with a compressor according to the invention, which depends on the amount of cooling fluid used. It requires less cooling fluid lines and thus increases the life of the compressor.
  • a longer at a lower flow rate remaining in an advantageously provided heat exchanger allows even with a smaller heat exchanger, the delivery of the heat absorbed by the compressor, which is already reduced by the heat input reducing coating anyway.
  • the heat-input-reducing coating must reduce the amount of heat introduced only to the extent that it can be removed from the cooling fluid.
  • the coating can be made of a less expensive material and / or in a lower thickness, which can advantageously reduce the rotating mass and thus the centrifugal forces on the compressor wheel.
  • a certain amount of heat input into the compressor wheel may be advantageous since this lowers the temperature of the compressed working medium and thus increases the degree of filling of the internal combustion engine.
  • the compressor wheel comprises a compressor hub and at least one compressor blade.
  • the compressor hub and / or the compressor blade can each be at least partially provided with the heat-transfer-reducing coating.
  • the heat-input-reducing coating extends from the leading edge of a partial blading to the wheel outlet.
  • the cooling fluid then no longer has to cool this area of the compressor wheel in particular, which, owing to the high rotational speeds present there, can simplify cooling, in particular the supply and removal of a cooling fluid directly acting upon the compressor wheel.
  • the entire rotating blading and the coming into contact with the working medium hub of the compressor wheel is provided with the heat input reducing coating, which the production of Coating can simplify - this can then be applied for example by immersion baths.
  • local heat peaks on uncoated areas can be prevented and thus a homogeneous temperature distribution within the compressor wheel can be achieved.
  • the heat input reducing coating is formed only on the surface of the compressor wheel facing a main flow of the working fluid to be compressed by the compressor. In this way, on the one hand, the heat input from the main flow of the compressed working medium can be reduced and thus the required amount of cooling fluid can be reduced with the aforementioned advantages. On the other hand, the heat dissipation from the compressor wheel to the adjacent part of the compressor housing is not impaired.
  • the heat input reducing coating comprises a ceramic layer which, due to its hardness and heat transfer coefficient, is particularly suitable for use in a compressor. This can be applied, for example, by thermal spraying, which allows the cost-effective production of a homogeneous coating with thin wall thickness and in particular the coating of selected partial areas of the blading.
  • any coating known as “thermal barrier coating” or “heat barrier coating” can be used, which can reduce the heat input into the compressor wheel, that is, in particular has a low heat transfer coefficient.
  • the content is expressly EP 0 211 032 B1, which generally describes such coatings.
  • the cooling fluid flows through a cavity in the compressor housing and thus indirectly cools the compressor wheel. D.-nn it dissipates heat from the part of the compressor housing adjacent to the compressor wheel. As a result, a medium is cooled in a gap, preferably a radial gap, between the compressor wheel and the compressor housing, which in turn cools the rear side of the compressor wheel adjacent thereto.
  • the radial gap between the compressor wheel and the compressor housing can be traversed by a leakage flow of the working medium which enters between the compressor wheel and the compressor housing. Without cooling, the compressor wheel would therefore be acted upon by heated working medium on the front and rear sides.
  • the heat introduced by the leakage flow itself is dissipated to the cooling fluid via the part of the compressor housing facing the radial gap, and heat from the compressor wheel to the cooling flow thus cooled and via this to the cooling fluid derived.
  • the heat input reducing coating is arranged only on the front of the compressor wheel facing the main flow of the working medium, that extends in particular from the leading edge of a partial blading to the wheel outlet, as this heat transfer to the medium in the radial gap and thus to the cooling fluid is not reduced and so the cooling is not affected.
  • the cavity may extend in the circumferential direction of the part of the compressor housing and have one or more feed and one or more outlets. If the cold cooling fluid is introduced at several points distributed over the circumference and / or the heated cooling fluid is discharged at a plurality of points distributed over the circumference, the compressor wheel can be cooled particularly uniformly and effectively.
  • the cavity can also have several parallel passages between inlet and outlet, in order to absorb as much heat as possible. to be able to.
  • the cavity can also have a turbulence-increasing geometry so as to increase the turbulence of the cooling fluid flow and thus its heat absorption.
  • the cooling fluid can also be introduced into the radial gap, where it can advantageously strike the rear side of the compressor wheel, take up heat therefrom and thus cool it directly. If a leakage flow of the working medium enters the radial gap, the cooling fluid introduced into the radial gap can be identical to the working medium, wherein it is advantageously introduced under higher pressure and thus bounces on the back of the compressor wheel. .
  • the cooling fluid at the back of the compressor wheel After the cooling fluid at the back of the compressor wheel has absorbed heat, it can advantageously flow into the main flow of the working fluid and thus reduce an undesirable leakage flow of the working fluid into the gap between compressor wheel and compressor housing. This can further reduce the amount of heat to be dissipated and thus the amount of cooling fluid required for this purpose, since the compressor wheel is then no longer or only to a lesser extent subjected to the hot working fluid at the rear.
  • the cooling fluid for the indirect cooling and the cooling fluid for the direct cooling may be identical, for example cold air, which may preferably be taken from a charge air cooler of the turbocharger. This advantageously simplifies the supply and discharge of the cooling fluid.
  • different cooling fluids can be used.
  • water which can preferably be removed from a cooling circuit of the internal combustion engine, flow through a cavity in the compressor housing and thus indirectly cool the compressor wheel, while air flows through the rear side of the compressor wheel through a separate supply line.
  • the fluids which are particularly suitable for the respective conditions that is to say, on the one hand the oncoming of the compressor impeller and on the other hand the heat dissipation by heat conduction and convection.
  • indirect cooling of the radial gap adjacent part of the compressor housing may have a fin arrangement for heat transfer into the cooling fluid. This advantageously increases the heat transfer surface and thus increases the heat dissipation.
  • such a rib arrangement can advantageously swirl the cooling fluid and thus increase its cooling effect.
  • the radial gap of the adjacent part of the compressor housing on a labyrinth seal for sealing a leakage flow.
  • a low-friction seal is created between the compressor housing and the compressor wheel rotating therein, which is not only wear-resistant and hence low-maintenance, but also generates no or only little frictional heat and thus additionally contributes to suppressing the temperature of the compressor wheel to maintain a permissible limit.
  • the labyrinth seal can also function as a rib arrangement and thus increase the heat transfer from the medium in the radial gap to the part of the compressor housing and into the cooling fluid.
  • the labyrinth seal may preferably be arranged in the region of the part of the compressor housing through which the cooling fluid flows.
  • FIG. 1 shows a part of a compressor according to a first embodiment of the present invention in a schematic lateral cross section.
  • Fig. 2 shows a part of a compressor according to a second embodiment of the present invention in a representation corresponding to Fig. 1;
  • 3 shows a part of a compressor according to a third embodiment of the present invention in a FIG. 1, 2 corresponding representation;
  • FIG. 4 shows a part of a compressor according to a fourth embodiment of the present invention in a FIGS. 1 -3 corresponding representation.
  • Fig. 1 shows schematically a part of a compressor according to a first embodiment of the present invention in a lateral cross-section.
  • the compressor comprises a compressor wheel 1, which is rotatably mounted in a compressor housing 11 and spaced therefrom by a radial gap 14.
  • a plurality of circumferentially curved compressor blades 12 are distributed over the circumference of a hub of the compressor wheel, of which only one can be seen in FIG.
  • the compressor blades 12 are provided with a heat input-reducing coating 2 made of aluminum oxide Al 2 O 3 , which extends in the exemplary embodiments from the leading edge 13 of a partial blading to the wheel outlet and is applied by thermal spraying. Although not visible in FIG. 1, the surface of the compressor hub is also provided with the coating in this area.
  • Air is accelerated by the compressor blades 12 radially and circumferentially and decelerated in a subsequent diffuser (not shown) and thereby compressed. It heats up especially in the area of the partial blading, in which energy is supplied by the acceleration. This heat is partly transferred to the compressor wheel, the temperature difference, which is proportional to the heat input, being highest in the area of the partial blading.
  • the heat transfer coefficient is smaller than that of an uncoated compressor wheel.
  • the heat input which is proportional to the heat transfer coefficient, is lower, so that less total heat is transferred from the compressed air into the compressor wheel.
  • the compressor housing 1 1 is preferably formed in two parts, wherein the Radi as a gap 14 facing part 6 and the other part of the compressor housing 11 each have a recess which define a cavity 4 in the assembled state.
  • the radial gap 14 facing part 6 at the other Part of the compressor housing 1 1 bolted (not shown) and the cavity 4 sealed by sealing rings 5 against the radial gap 14.
  • cold water from an engine cooling circuit flows into the cavity, flows through it and is discharged through a discharge (not shown) back out of the compressor housing.
  • the water absorbs heat from the air heated by compression, which enters the radial gap 14 from a main flow along the blades 12 as a leakage flow between the compressor wheel 1 and the compressor housing 1.
  • the part 6 in the region of the cavity 4 has an arrangement of cooling fins 7, which increase the heat-transmitting surface and in addition can increase the turbulence of the leakage flow and thus the heat transfer by convection. Subsequently, the water thus heated in a heat exchanger arranged outside the compressor (not shown) is cooled again.
  • the compressed and thus heated air of the leakage flow is cooled, thus avoiding heating of the rear side of the compressor wheel 1 facing the radial gap 14.
  • the thus cooled leakage flow absorbs heat from the compressor wheel and transfers it to the water flowing through the cavity 4.
  • the compressor wheel 1 is cooled indirectly via the air in the radial gap 14, the rib arrangement 7 and the water flowing through the cavity 4.
  • Fig. 2 shows a part of a compressor according to a second embodiment of the present invention in a representation corresponding to Fig. 1. In the following, only the differences from the first embodiment will be discussed, while the rest, insofar identical features are referred to the above description.
  • the cavity 4 with the back of the compressor wheel 1 a labyrinth seal 8.
  • This one hand reduces the leakage flow of hot, compressed air from the main flow into the radial gap 14, so that the back of the compressor wheel 1 is not or only slightly acted upon by hot air, which already advantageously reduces the heat input into the compressor wheel and thus to the indirect Kü 'ment required amount of coolant fluid.
  • the labyrinth arrangement 8 which is formed in the region of the cavity 4 through which water flows, acts like the cooling rib arrangement 7 described in connection with the first embodiment.
  • Fig. 3 shows a part of a compressor according to a third embodiment of the present invention. Again, only the differences from the above-described embodiments will be discussed below and, moreover, their description is referred to.
  • a direct cooling of the compressor impeller 1 is provided.
  • the part 6 of the compressor housing 11 has a plurality of axial bores 10 distributed in the circumferential direction, which communicate with the cavity 4, which, in contrast to the first and second embodiments, has no discharge lines.
  • the cooling air is taken from a charge air cooler, not shown, introduced via the supply line 3 under pressure in the cavity 4, flows from this through the axial bores 10 and bounces on the radial gap 14 facing the rear of the compressor wheel 1. There it absorbs heat from the compressor and then flows out of the radial gap into the main flow of the working medium.
  • a charge air cooler not shown
  • Fig. 4 shows a part of a compressor according to a fourth embodiment of the present invention. While in the following only the differences to the above-mentioned explanations will be discussed, reference may be made to the previous description.
  • a labyrinth seal which reduces the entry of a leakage flow into the radial gap 14 (see also the second embodiment).
  • this labyrinth seal distributed over the circumference a plurality of circumferentially extending slots 9 are formed, which communicate with the cavity 4.
  • cold air which then impinges on the rear side of the compressor wheel 1, flows through it, cools the latter and then discharges it into the main flow of the working medium.
  • the flow exiting through the slots 9 in this area is swirled in cool air, which increases the heat transfer between it and the compressor and so beneficial its cooling further amplified, so that here too with a smaller amount of cooling air, the temperature of the inventively coated compressor wheel below a maximum allowable temperature of for example 200 0 C can be maintained.
  • the reduction in the amount of cooling air in turn increases the efficiency of the compressor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un compresseur, en particulier un compresseur radial, pour un turbocompresseur à suralimentation, lequel comprend une roue à aubes de compresseur (1) qui est logée de manière rotative dans une caisse de compresseur, un élément (6) voisin de la roue à aubes de compresseur de la caisse de compresseur étant parcouru par un fluide de refroidissement. La roue à aubes de compresseur est munie au moins partiellement d'un revêtement (2) réduisant la transmission de chaleur.
PCT/EP2007/008804 2006-10-12 2007-10-10 Compresseur pour un turbocompresseur à suralimentation et son procédé de refroidissement WO2008043539A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CH00609/09A CH698234B1 (de) 2006-10-12 2007-10-10 Verdichter für einen Turbolader sowie Verfahren zu dessen Kühlung.
JP2009531768A JP2010506091A (ja) 2006-10-12 2007-10-10 ターボチャージャのためのコンプレッサ及びその冷却方法

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006048784.2 2006-10-12
DE102006048784A DE102006048784A1 (de) 2006-10-12 2006-10-12 Verdichter für einen Turbolader sowie Verfahren zu dessen Kühlung

Publications (1)

Publication Number Publication Date
WO2008043539A1 true WO2008043539A1 (fr) 2008-04-17

Family

ID=38826577

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2007/008804 WO2008043539A1 (fr) 2006-10-12 2007-10-10 Compresseur pour un turbocompresseur à suralimentation et son procédé de refroidissement

Country Status (6)

Country Link
JP (1) JP2010506091A (fr)
KR (1) KR20090082890A (fr)
CN (1) CN101631940A (fr)
CH (1) CH698234B1 (fr)
DE (1) DE102006048784A1 (fr)
WO (1) WO2008043539A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009034962B3 (de) * 2009-07-28 2011-01-13 Man Diesel & Turbo Se Radialverdichter
GB2475533A (en) * 2009-11-21 2011-05-25 Cummins Turbo Tech Ltd Compressor wheel
DE102010037356B4 (de) * 2010-09-06 2013-09-05 Kompressorenbau Bannewitz Gmbh Verdichterradkühlung
GB2531980A (en) * 2009-11-21 2016-05-04 Cummins Turbo Tech Ltd Compressor wheel
US9377025B2 (en) 2011-12-06 2016-06-28 Hyundai Motor Company Compressor housing and two-stage turbocharger thereof
US20220081763A1 (en) * 2020-09-17 2022-03-17 Applied Materials, Inc. Aluminum oxide protective coatings on turbocharger components and other rotary equipment components

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009024679B4 (de) 2009-06-12 2016-04-07 Man Diesel & Turbo Se Verdichterlaufrad und damit ausgerüsteter Radialverdichter
FR2960923B1 (fr) 2010-06-08 2013-12-20 Snecma Controle de la poussee axiale par guidage de l'air preleve sur un compresseur centrifuge
JP5700999B2 (ja) * 2010-10-06 2015-04-15 三菱重工業株式会社 遠心圧縮機
DE102010042104A1 (de) 2010-10-07 2012-04-26 Bayerische Motoren Werke Aktiengesellschaft Abgasturbolader
GB2499627A (en) * 2012-02-23 2013-08-28 Napier Turbochargers Ltd Turbocharger casing
JP2014111905A (ja) * 2012-12-05 2014-06-19 Mitsubishi Heavy Ind Ltd 遠心圧縮機およびこれを備えた過給機ならびに遠心圧縮機の運転方法
DE102012024314A1 (de) 2012-12-13 2014-06-18 Daimler Ag Turbolader für einen Energiewandler
DE102013203455A1 (de) * 2013-02-28 2014-08-28 Abb Turbo Systems Ag Zwischenwand zur Abdichtung des Rückraums eines Radialverdichters
DE102013013235A1 (de) * 2013-08-08 2015-02-12 Man Diesel & Turbo Se Abschlussdeckel für ein Verdichterlaufrad eines Abgasturboladers und Abgasturbolader
JP6382120B2 (ja) * 2015-01-26 2018-08-29 三菱重工業株式会社 排気タービン過給機
DE102016213238A1 (de) * 2016-07-20 2018-01-25 Man Diesel & Turbo Se Radialturbinenrotor und Verfahren zum Herstellen desselben
JP6899232B2 (ja) * 2017-03-07 2021-07-07 三菱重工業株式会社 電動過給機
CN107448417B (zh) * 2017-09-01 2020-01-17 西北工业大学 离心压气机及叶轮冷却装置
JP6953556B2 (ja) 2017-12-25 2021-10-27 三菱重工エンジン＆ターボチャージャ株式会社 コンプレッサホイールおよび過給機
KR102075550B1 (ko) * 2018-09-19 2020-02-11 한국과학기술원 순산소 연소 발전 시스템
DE102021127333A1 (de) * 2021-10-21 2023-04-27 Ihi Charging Systems International Gmbh Aufladesystem einer Brennstoffzelle

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB705387A (en) * 1951-02-15 1954-03-10 Power Jets Res & Dev Ltd Improvements relating to radial-flow turbine or centrifugal compressors
DE966394C (de) * 1951-11-18 1957-08-01 Bayerische Motoren Werke Ag Abgasturbolader fuer Brennkraftmaschinen
DE4417095A1 (de) * 1994-05-16 1995-11-23 Abb Management Ag Verdichterrad
DE19653217A1 (de) * 1995-12-20 1997-06-26 Hitachi Ltd Turbolader für Verbrennungsmotoren
EP1541717A2 (fr) * 2003-11-22 2005-06-15 DaimlerChrysler AG Procédé de fabrication de composants en métaux légers recouverts qui sont disposés dans un courant de fluide turbulent

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2975959A (en) * 1958-09-30 1961-03-21 Berry W Foster Back-to-back centrifugal compressor and centripetal turbine having an integral rotordisc
JPS60164602U (ja) * 1984-04-10 1985-11-01 三菱レイヨン株式会社 タ−ボチヤ−ジヤ用ロ−タ−
JPS62211389A (ja) * 1986-03-12 1987-09-17 Hitachi Ltd セラミツク被覆タ−ボチヤ−ジヤ−及びその製造方法
DE19652754A1 (de) * 1996-12-18 1998-06-25 Asea Brown Boveri Abgasturbolader
JP2000291441A (ja) * 1999-04-01 2000-10-17 Toyota Motor Corp ターボチャージャのインペラ
JP2003525377A (ja) * 1999-10-20 2003-08-26 アーベーベー ターボ システムズ アクチエンゲゼルシャフト ターボ機械のロータとステータとの間に形成されたラジアルギャップの流れを間接的に冷却する方法と装置
US6375425B1 (en) * 2000-11-06 2002-04-23 General Electric Company Transpiration cooling in thermal barrier coating
EP1317995A1 (fr) * 2001-12-05 2003-06-11 Siemens Aktiengesellschaft Procédé et dispositif de lissage de surface d'une aube de turbine à gaz
DE202005019320U1 (de) * 2005-12-08 2006-02-09 Abb Turbo Systems Ag Abgasturbine mit Wärmeschutz

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB705387A (en) * 1951-02-15 1954-03-10 Power Jets Res & Dev Ltd Improvements relating to radial-flow turbine or centrifugal compressors
DE966394C (de) * 1951-11-18 1957-08-01 Bayerische Motoren Werke Ag Abgasturbolader fuer Brennkraftmaschinen
DE4417095A1 (de) * 1994-05-16 1995-11-23 Abb Management Ag Verdichterrad
DE19653217A1 (de) * 1995-12-20 1997-06-26 Hitachi Ltd Turbolader für Verbrennungsmotoren
EP1541717A2 (fr) * 2003-11-22 2005-06-15 DaimlerChrysler AG Procédé de fabrication de composants en métaux légers recouverts qui sont disposés dans un courant de fluide turbulent

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009034962B3 (de) * 2009-07-28 2011-01-13 Man Diesel & Turbo Se Radialverdichter
GB2475533A (en) * 2009-11-21 2011-05-25 Cummins Turbo Tech Ltd Compressor wheel
US20110229338A1 (en) * 2009-11-21 2011-09-22 Michael Voong Compressor wheel
US9234525B2 (en) 2009-11-21 2016-01-12 Cummins Turbo Technologies Limited Compressor wheel
GB2475533B (en) * 2009-11-21 2016-04-13 Cummins Turbo Tech Ltd Compressor wheel
GB2531980A (en) * 2009-11-21 2016-05-04 Cummins Turbo Tech Ltd Compressor wheel
GB2531980B (en) * 2009-11-21 2016-08-10 Cummins Turbo Tech Ltd Compressor wheel
DE102010037356B4 (de) * 2010-09-06 2013-09-05 Kompressorenbau Bannewitz Gmbh Verdichterradkühlung
US9377025B2 (en) 2011-12-06 2016-06-28 Hyundai Motor Company Compressor housing and two-stage turbocharger thereof
US20220081763A1 (en) * 2020-09-17 2022-03-17 Applied Materials, Inc. Aluminum oxide protective coatings on turbocharger components and other rotary equipment components

Also Published As

Publication number Publication date
DE102006048784A1 (de) 2008-04-17
CH698234B1 (de) 2010-10-15
CN101631940A (zh) 2010-01-20
JP2010506091A (ja) 2010-02-25
KR20090082890A (ko) 2009-07-31

Similar Documents

Publication Publication Date Title
WO2008043539A1 (fr) Compresseur pour un turbocompresseur à suralimentation et son procédé de refroidissement
DE102011053930B4 (de) Vorrichtung und Verfahren zur Kühlung von Plattformabschnitten von Turbinenrotorschaufeln
EP0957237B1 (fr) Refroidissement d'un joint à nid d'abeille dans une turbine à gaz
EP1191189A1 (fr) Aube de turbine à gaz
CH681243A5 (fr)
DE112011104298B4 (de) Gasturbinenmotor mit Sekundärluftstromkreis
DE4102033A1 (de) Duesenbandkuehlung
EP3440319B1 (fr) Turbocompresseur pour un moteur à combustion interne
EP2044293B1 (fr) Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation
CH708795A2 (de) Segment für ein ringförmiges Rotationsmaschinen-Leitradbauteil.
EP3115558B1 (fr) Aube directrice d'une turbine à gaz
EP0900322A1 (fr) Arbre de turbine et procede de refroidissement d'un arbre de turbine
DE1601563C3 (de) Luftgekühlte Laufschaufel
DE102019108588A1 (de) Verbrennungsmotor
DE102015107979A1 (de) Kühlversorgungskreis für Turbomaschinen
EP3452702B1 (fr) Carter de turbine pour turbocompresseur de moteur à combustion interne et turbocompresseur
WO1998013584A1 (fr) Compensation de la perte de pression d'une conduite d'air de refroidissement dans une installation de turbine a gaz
DE112012004417T5 (de) Rotationskolben-Verbrennungsmotor
WO2001016467A1 (fr) Turbine et procede pour evacuer du fluide de fuite
EP3006668A1 (fr) Turbine à gaz dotée de deux alimentations en vortex destinées au refroidissement du rotor
DE2947439C2 (de) Gasturbinentriebwerk
EP1734292A1 (fr) Dispositif d'étanchéité pour une turbomachine
DE102016202741A1 (de) Rotor und elektrische Maschine
DE102016004936B4 (de) Elektrische Maschine
EP1697652B1 (fr) Embrayage hydrodynamique

Legal Events

Date Code Title Description
WWE Wipo information: entry into national phase

Ref document number: 200780045671.8

Country of ref document: CN

121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 07818877

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 2009531768

Country of ref document: JP

Kind code of ref document: A

WWE Wipo information: entry into national phase

Ref document number: 1020097009541

Country of ref document: KR

122 Ep: pct application non-entry in european phase

Ref document number: 07818877

Country of ref document: EP

Kind code of ref document: A1