EP1706595B1 - Turbomachine comprenant un canal en spirale dans la partie mediane du carter - Google Patents

Turbomachine comprenant un canal en spirale dans la partie mediane du carter Download PDF

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Publication number
EP1706595B1
EP1706595B1 EP04818152A EP04818152A EP1706595B1 EP 1706595 B1 EP1706595 B1 EP 1706595B1 EP 04818152 A EP04818152 A EP 04818152A EP 04818152 A EP04818152 A EP 04818152A EP 1706595 B1 EP1706595 B1 EP 1706595B1
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EP
European Patent Office
Prior art keywords
turbine
housing
compressor
spiral
turbo
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.)
Active
Application number
EP04818152A
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German (de)
English (en)
Other versions
EP1706595A1 (fr
Inventor
Karl-Ernst Hummel
Stephan Wild
Günter Kröger
Norbert Poppenborg
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.)
Mann and Hummel GmbH
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Mann and Hummel GmbH
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Publication date
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Publication of EP1706595A1 publication Critical patent/EP1706595A1/fr
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Publication of EP1706595B1 publication Critical patent/EP1706595B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • 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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to a turbomachine for generating a mass flow according to the preamble of claim 1.
  • a turbine housing for an exhaust gas turbocharger in which an exhaust-driven turbine rotor drives a compressor rotor.
  • the compressor rotor is connected by a rigid shaft to the turbine rotor.
  • the shaft, which carries the compressor wheel and the turbine wheel, is mounted in a middle part of the housing, which is closed on the turbine side by a turbine housing and on the compressor side by a compressor housing.
  • the exhaust gas flows tangentially into a spiral, narrowing contour of the turbine housing and is directed to turbine blades of the turbine rotor. These turbine blades drive the turbine rotor.
  • the exhaust stream continues to flow axially from the turbine housing to the turbine wheel.
  • spiral channels require a high geometric and surface requirement.
  • the spiral channels are formed in a turbine housing and a compressor housing. These two housings are laterally flanged to a middle part of the housing. This configuration can only be produced due to the shaping with high production engineering effort.
  • the expert takes from the US 4598542 , of the GB 1315307 , of the US 4009568 and the US 3844676 Turbines and compressors in different construction variants, in which the compressor or turbine channels are arranged in each case at least two housing parts. Again, therefore, a very high component and fit accuracy is required.
  • the post-published font EP 1394366 A shows a turbomachine with a surrounding a storage space
  • Housing which is at least partially formed integrally with the housing surrounding at least one of the rotor chambers.
  • the object of the present invention is to change the design of the housing elements such that the production of the spiral channels can be simplified.
  • the inventive arrangement of the turbomachine is based on the laying of at least one spiral geometry in a middle part of the housing. This forms thereby at least a part of a turbine or a compressor housing.
  • the spiral geometry is closed on the outside by a lid.
  • a cross section of the spiral channel is defined by the middle part of the housing and the cover.
  • a parting plane Between the cover and the middle part of the housing is a parting plane, which is aligned perpendicular to a turbine shaft mounted in the middle part of the housing.
  • the turbomachine can be, for example, a turbomachine, for example, as an exhaust gas turbocharger or a secondary air charger for secondary air injection in catalytic converters. However, it can also be used as a simple turbine for converting a mass flow into a rotor movement.
  • the turbomachine according to the invention advantageously makes it possible to lay a spiral contour in the central housing middle part, thereby the flow cross-section of the spiral contour can be produced undercut-free in the primary molding process. Furthermore, results from the narrower design of the lid, a reduced space requirement.
  • the lid is flat on the area adjacent to the spiral contour.
  • the spiral contour is formed exclusively in the middle part.
  • the contour corresponding to the turbine rotor and the axial inlet or outlet connection can be carried out unchanged.
  • This embodiment advantageously makes it possible to meet the high requirement of the spiral geometry in terms of geometry and dimensional tolerance. Due to the simple geometry of the lid this can also be made of plastics, such as polyamide.
  • the spiral geometries of the turbine and the compressor side are arranged in the middle part of the housing. As a result, the length of the turbine shaft and thus the entire housing can be shortened. Thus, the required space is further reduced.
  • An advantageous embodiment of the invention relates to the cross-sectional profile of the spiral channel, in particular on the turbine side.
  • the widening of the cross section of the spiral channel can be effected by an axial and a radial expansion. If the expansion is achieved by radial expansion, so reduces the axial depth of the spiral channel. This increases the outer circumference of the spiral channel. Since this circumference of the spiral channel on the turbine side is smaller compared to the compressor side, there is sufficient space available in the radial direction. Thus, the entire housing can be made shorter.
  • a further advantageous variant relates to the rotational position of the spiral channels to each other. Due to the reduced axial depth of the spiral channels, any desired rotational position of the spiral channels relative to one another can be achieved. This is advantageous because often only very much for the tangential arrival or Abströmstutzen limited installation space is available. These can thus be arranged at any angle to each other.
  • At least one tangential nozzle is angled parallel to the turbine shaft.
  • the tangential connection piece is preferably angled against the respective cover side.
  • Another design provides to arrange the tangential nozzle in variable angle to the turbine shaft. Manufacturing technology, this variant is realized by side shift.
  • the possible Angular range is approx. 0-90 °. This makes it advantageously possible to make the angle of attack of the tangential nozzle to the turbine shaft variable.
  • one or both tangential nozzles are integrally formed on the cover of the respective side. According to the above-mentioned angle design, this can be realized by a double-shell mold or with a side slide manufacturing technology. Advantageous is the possibility of further adaptation of the tangential nozzle to the geometry of the installation space.
  • the dividing plane present between housing center part and cover is arranged substantially centrally in the flow cross-section of the spiral channels.
  • a spiral channel in its axial position toward the turbine shaft can be arranged substantially in the cover in a partial area substantially in the middle part of the housing and in a further partial area.
  • this makes it possible to use both the cover and the middle part of the housing for the arrangement of the spiral contours.
  • aerodynamically optimized geometries can be formed.
  • a turbomachine 10 according to the invention is shown in full section, in which in a central housing middle part 11, a turbine shaft 12 is mounted. On the turbine shaft 12, a compressor rotor 13 and on the opposite side of a turbine rotor 14 is rigidly fixed.
  • the housing middle part 11 is closed on the opposite sides by a turbine cover 16 and a compressor cover 15. These two covers 15, 16 are tensioned on plane-shaped parting planes 21, 22 on the middle part of the housing.
  • spiral channels 17, 18 are formed on both sides, these spiral channels are closed to the lid sides on the plane-shaped parting planes 21, 22 through the lid 15,16. Between the parting planes 21, 22, the middle part of the housing has a housing thickness a.
  • spiral channels 17,18 change their circular cross-sectional area in a spiral shape and overlap in the axial direction of the turbine shaft 12 with the dimension x in the region of the largest cross-sectional area.
  • a discharge nozzle 24 is arranged to a turbine-side downstream side 19
  • the compressor cover 15 is arranged to a compressor-side upstream side of a 20 axial flow connection 23.
  • FIG. 2 shows a further flow machine 10 in full section.
  • the spiral channels 17a, 18a in contrast to FIG. 1 designed in an oval shape.
  • this oval configuration of the spiral channels 17a, 18a need not be made over the entire length, but may also be formed only in the region of the largest cross-sectional area or only on one side of the housing. Due to the oval design of the spiral channels 17a, 18a, the housing thickness a can be reduced.
  • FIG. 3a shows a further full section through a turbomachine 10.
  • a turbine-side inflow pipe 25 and a compressor-side outflow pipe 26 are shown.
  • the spiral channels 17, 18 are partially shown as dashed lines.
  • the two sockets 25, 26 are arranged tangentially to the spiral channels 17, 18 and correspond with them.
  • FIG. 3b shows the housing middle part 11 according to the FIG. 3a in the plan view.
  • the components corresponding to the preceding figures are given the same reference numerals.
  • the course of the turbine-side spiral channel 17 is shown as a dashed line.
  • the middle part 11 is shown in partial section.
  • the sockets 25, 26 are arranged at an angle of 180 ° to each other.
  • the housing thickness a (FIG. Fig. 3a ) are increased in order to avoid an overlap of the spiral channels 17, 18.
  • the sockets 26, 25 of the housing middle part 11 are arranged at an angle of approximately 270 ° to each other, by crossing the two sockets 25b, 26b. This is the most unfavorable angular position, because the housing thickness a of the inner diameter c of the nozzle 25b, 26b is determined. In order to minimize the housing thickness a in this angular position, the sockets 25b, 26b are designed in the crossing region with an oval cross-section.
  • FIG. 4 shows the middle part 11 viewed in perspective on the compressor side.
  • the dashed line shows the circular design of the compressor-side spiral channel 18 and the solid line of the oval spiral channel 18b. Due to the oval design results over the entire geometry of the spiral channel 18b a larger width b. This may require a larger case diameter. Due to the smaller cross-sectional area of the turbine-side spiral channel 17 (FIG. FIG. 3 ), only this oval and thus wider can be designed. As a result, a uniform housing diameter can be produced.
  • FIGS. 5a and 5b each show a partial section of the housing middle part 11 according to the FIG. 4 Cut CC and DD.
  • the width b of the oval spiral channel 18b is shown with respect to the dashed line width of the circular spiral channel 18.
  • the turbomachine in two variants shown schematically in full section.
  • the two tangential stubs 125, 126 are angled at right angles to the parting planes 121, 122.
  • both nozzles 125, 126 directed against the side of their respective spiral channels 117, 118.
  • the two covers 115, 116 close the two spiral channels 117, 118 to the region of the two stubs 125, 126.
  • the spiral channels 117, 118 and the two stubs 125, 126 designed undercut. This allows a simple production method in the original molding process.
  • FIG. 7 a further variant of the turbomachine 10 is shown schematically.
  • the nozzle 226 is in this case arranged on the housing middle part 211, and angled at right angles to the separating plane 222 in the direction of the compressor-side spiral channel 218.
  • the spiral channel 218 is closed by the compressor cover 215.
  • the undercut formed in the housing middle part 211 can be produced, for example, in the original molding process by a tool with a drag slider.
  • the housing middle part 211 is closed by the turbine cover 216.
  • FIG. 8 schematically shows the turbomachine 10.
  • the nozzle 326 is in this case arranged on the cover 315 and corresponds to the parting plane 322 with the spiral channel 317.
  • the middle part 311 thus forms only the spiral contour 317 and can be made without the form-technically complicated nozzle 326.
  • On the turbine side of the housing middle part 311 is closed by the turbine cover 316.
  • FIG. 9 shows a turbomachine 10 at which the dividing plane 22 extends substantially centrally through the cross section of the compressor-side spiral channel 18b.
  • the spiral channel 18b extends in the compressor cover 15 parallel to the parting plane 22 and angled in the middle part 11 to the parting plane 22. Therefore, the parting plane 22 is arranged in the embodiment shown only in a partial region in the middle in the spiral channel 18b.
  • the geometrically simple part can be formed for example by a simple plan-shaped groove in the compressor cover 15 and the geometrically complex and precise shape be placed in the middle part 11.
  • the two covers 15, 16 are preferably made of a plastic, wherein the housing middle part 11 is preferably formed of a metallic material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Details Of Aerials (AREA)
  • Control Of Motors That Do Not Use Commutators (AREA)
  • Discharge Lamps And Accessories Thereof (AREA)

Claims (7)

  1. Turbomachine en vue de la génération d'un flux massique, présentant une partie centrale de carter dans laquelle est logé un arbre de turbine,
    la partie centrale de carter étant moulée comme partie d'un carter de turbine du côté turbine et comme partie d'un carter de compresseur du côté compresseur, une tubulure d'admission étant disposée sur la partie centrale de carter, du côté turbine en sens tangentiel de l'arbre de turbine, et une tubulure de sortie étant disposée en sens axial sur le carter de turbine,
    une tubulure de sortie étant disposée sur la partie centrale de carter, du côté compresseur en sens tangentiel, et une tubulure d'admission étant disposée sur le carter de compresseur en sens axial sur le carter de compresseur,
    un couvercle étant prévu respectivement du côté compresseur et/ou du côté turbine et ce couvercle étant réalisé comme partie du carter, caractérisé en ce que le canal en spirale pour le côté turbine et/ou le côté compresseur est prévu dans la partie centrale du carter, le couvercle étant réalisé, dans la zone adjacente au contour en spirale - hormis le contour qui communique avec la roue du rotor -, par une surface s'étendant en sens radial sur un seul plan.
  2. Turbomachine selon la revendication 1, les deux canaux en spirale étant formés par des parties de la partie centrale de carter et du couvercle.
  3. Turbomachine selon l'une des revendications précédentes, le canal en spirale présentant, notamment du côté turbine, une certaine profondeur maximum en direction de l'arbre de turbine, une modification de la section pouvant être réalisée par un élargissement du canal en spirale en sens radial par rapport à l'arbre de turbine.
  4. Turbomachine selon la revendication 3, les canaux en spirale étant disposés, en raison de leur certaine profondeur maximum, à une position rotatrice quelconque l'un par rapport à l'autre, de sorte que les raccords tangentiels puissent être positionnés à un angle quelconque l'un de l'autre.
  5. Turbomachine selon l'une des revendications précédentes, au moins un raccord étant coudé et évoluant de manière parallèle à l'arbre de la turbine.
  6. Turbomachine selon la revendication 5, les raccords tangentiels étant disposés à un angle variable par rapport à l'axe de l'arbre de la turbine.
  7. Turbomachine selon l'une des revendications précédentes, les raccords tangentiels étant disposés sur le couvercle du côté turbine et/ou sur le couvercle du côté compresseur.
EP04818152A 2003-11-04 2004-11-03 Turbomachine comprenant un canal en spirale dans la partie mediane du carter Active EP1706595B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10352156 2003-11-04
PCT/EP2004/052774 WO2005045201A1 (fr) 2003-11-04 2004-11-03 Turbomachine comprenant un canal en spirale dans la partie mediane du carter

Publications (2)

Publication Number Publication Date
EP1706595A1 EP1706595A1 (fr) 2006-10-04
EP1706595B1 true EP1706595B1 (fr) 2010-09-22

Family

ID=34559483

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04818152A Active EP1706595B1 (fr) 2003-11-04 2004-11-03 Turbomachine comprenant un canal en spirale dans la partie mediane du carter

Country Status (6)

Country Link
US (1) US8062006B2 (fr)
EP (1) EP1706595B1 (fr)
JP (1) JP4638878B2 (fr)
AT (1) ATE482326T1 (fr)
DE (1) DE502004011691D1 (fr)
WO (1) WO2005045201A1 (fr)

Families Citing this family (12)

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Publication number Priority date Publication date Assignee Title
DE102008008856A1 (de) * 2008-02-13 2009-08-20 Daimler Ag Turbinengehäuse und Verfahren zum Herstellen eines Turbinengehäuses
KR101737136B1 (ko) * 2009-04-22 2017-05-17 디에스엠 아이피 어셋츠 비.브이. 반경류 압축기의 플라스틱 하우징
DE102009035573A1 (de) 2009-07-31 2011-02-10 Man Diesel & Turbo Se Radialkompressor und Verfahren zum Herstellen eines Radialkompressors
CN103154522A (zh) 2010-07-21 2013-06-12 Itt制造企业有限责任公司 用于旋转固体处理装备的磨损减少装置
EP2655829B1 (fr) * 2010-12-22 2015-04-01 Honeywell International Inc. Ensemble de culasse de moteur et turbocompresseur
US20120186247A1 (en) * 2011-01-26 2012-07-26 Honeywell International Inc. Turbocharger with Reversed Compressor Volute Optionally Integrated into the Center Housing
DE102011075449A1 (de) * 2011-05-06 2012-11-08 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader
US8955318B2 (en) 2012-03-21 2015-02-17 Honeywell International Inc. Turbocharger cartridge and engine cylinder head assembly
US9091200B2 (en) 2012-03-21 2015-07-28 Honeywell International Inc. Turbocharger and engine cylinder head assembly
US8966895B2 (en) 2012-03-21 2015-03-03 Honeywell International Inc. Turbocharger cartridge, bypass, and engine cylinder head assembly
US8966894B2 (en) 2012-03-21 2015-03-03 Honeywell International Inc. Turbocharger cartridge and engine cylinder head assembly
DE102016209951A1 (de) * 2016-06-07 2017-12-07 Ford Global Technologies, Llc Zusammengesetztes Turbinengehäuse

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Publication number Priority date Publication date Assignee Title
US2456128A (en) * 1946-11-15 1948-12-14 Tri Clover Machine Co Pump and impeller therefor
GB1315307A (en) 1969-08-21 1973-05-02 Cav Ltd Turbo superchargers for internal combustion engines
GB1426554A (en) 1972-04-13 1976-03-03 Cav Ltd Turbo superchargers for internal combustion engines
US4009668A (en) 1975-07-07 1977-03-01 Deere & Company Planter apparatus and method for planting
US4009568A (en) 1975-10-30 1977-03-01 General Motors Corporation Turbine support structure
GB2153437A (en) * 1984-01-07 1985-08-21 Rolls Royce Improvements in or relating to gas turbine power plant
US5951019A (en) 1996-09-05 1999-09-14 Centre For Engineering Research Inc. Method of forming a metal-to-metal seal in high pressure applications with low contact stress
GB0121864D0 (en) 2001-09-10 2001-10-31 Leavesley Malcolm G Turbocharger apparatus
DE50209663D1 (de) * 2002-09-02 2007-04-19 Borgwarner Inc Gehäuse für Strömungsmaschinen

Also Published As

Publication number Publication date
US20080034754A1 (en) 2008-02-14
EP1706595A1 (fr) 2006-10-04
ATE482326T1 (de) 2010-10-15
JP4638878B2 (ja) 2011-02-23
DE502004011691D1 (de) 2010-11-04
WO2005045201A1 (fr) 2005-05-19
US8062006B2 (en) 2011-11-22
JP2007510854A (ja) 2007-04-26

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