EP1383987B1 - Berstschutzvorrichtung für radialverdichter von turboladern - Google Patents

Berstschutzvorrichtung für radialverdichter von turboladern Download PDF

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Publication number
EP1383987B1
EP1383987B1 EP02719599A EP02719599A EP1383987B1 EP 1383987 B1 EP1383987 B1 EP 1383987B1 EP 02719599 A EP02719599 A EP 02719599A EP 02719599 A EP02719599 A EP 02719599A EP 1383987 B1 EP1383987 B1 EP 1383987B1
Authority
EP
European Patent Office
Prior art keywords
wall
compressor
burst
protection arrangement
insert wall
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.)
Expired - Lifetime
Application number
EP02719599A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1383987A1 (de
Inventor
Zhanjun Hou
Josef Bättig
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems AG
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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Publication of EP1383987A1 publication Critical patent/EP1383987A1/de
Application granted granted Critical
Publication of EP1383987B1 publication Critical patent/EP1383987B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F02B39/16—Other safety measures for, or other control of, 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • F05B2260/3011—Retaining bolts or nuts of the frangible or shear type
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical

Definitions

  • the invention relates to a burst protection device of a radial compressor of a turbocharger, as described by the features of the preamble of claim 1 and a turbocharger according to the features of the preamble of claim 9.
  • Ver Whyrradberstens represents for the people and objects located in the vicinity of the turbocharger a significant risk, since the fragments of the compressor wheel can penetrate the outer walls of the exhaust gas turbocharger with their large kinetic energy. Flying debris can be fatal to humans and cause significant damage to neighboring facilities.
  • EP-0 908 629 it has been proposed, at a diffuser flange of a compressor wheel, which is located between the compressor wheel and turbine wheel and which is connected in the outer region with the compressor housing and in the inner region with the bearing housing, a predetermined breaking point in the form of a circular groove between provided in the inner and outer regions, so that in case of bursting of the compressor wheel in the radial direction accelerated fragments can not penetrate the compressor housing. An axial ejection of fragments is not prevented by the predetermined breaking point.
  • the compressor wheel acts as a wedge between a compressor diffuser adjacent to the compressor wheel downstream in the flow channel and an insert wall bounding the flow channel radially outside in the area above the laul paddles of the compressor.
  • This axially acting force is transmitted through the insert wall to the compressor housing and further to the connection between the compressor housing and an upstream component, such as a compressor. an intake manifold or a filter silencer.
  • an upstream component such as a compressor. an intake manifold or a filter silencer.
  • the connection between the compressor housing and the upstream component which is usually a screw, these large axial forces can not withstand and parts of the compressor housing and the upstream component are thrown axially. The resulting danger to people and neighboring facilities can not counteract the above-mentioned measures.
  • the inventive bursting protection device of a radial compressor of a turbocharger has a flow channel, which is bounded by the rotor blades of the compressor wheel through an insert wall radially outwards.
  • the insert wall has a predetermined breaking point over the blades or further downstream. In the case of a compressor wheel rupture, a part of the axial forces is absorbed by the controlled breaking of the insert wall at the predetermined breaking point.
  • the connection between the compressor housing and upstream component is not destroyed and the individual parts can no longer be thrown axially.
  • the insert wall is surrounded radially by an inner wall of the compressor housing and has at least a first conically tapering upstream section, this section begins approximately at the height of the predetermined breaking point of the insert wall and there has an initial radius of about the same size or slightly larger than that Radius of the insert wall at the predetermined breaking point is.
  • the terminating part of the insert wall which moves in the axial direction because of the absorption of a large part of the axial kinetic energy, is braked in its axial movement by this first section of the inner wall tapering conically upstream in the axial direction. By deformation of this section of the inner wall and by friction losses, axial kinetic energy is destroyed.
  • the predetermined breaking point is arranged in the region between the rotor blades of the compressor wheel and downstream adjacent vanes of a compressor diffuser. This arrangement of the predetermined breaking point leads to the absorption of most of the axial energy in the terminating part of the insert wall.
  • the predetermined breaking point is designed in the form of a notch. This is easy to manufacture, inexpensive and allows a very defined breakage of the wall of use.
  • the first, tapered upstream tapering portion of the inner wall with a pitch in the range approximately between 5 ° and 20 ° to design. In this way, a large part of the axial kinetic energy can be destroyed and at the same time ensured that the inner wall is only deformed and will not penetrate.
  • brake elements projecting radially outward from the insert wall are provided which cooperate in the case of the compressor wheel rasp with further conically tapering sections of the inner wall.
  • one or more of the conically tapered sections as radially inwardly projecting brake lugs from the inner wall.
  • the brake lugs can be deformed without this having a deforming effect on the adjacent conical sections.
  • FIG. 1 shows in section along its machine axis 10 a compressor-side section of a turbocharger with a radial compressor 12.
  • the radial compressor 12 has a compressor wheel 14 mounted on a shaft 13 with rotor blades 16.
  • the blades 16 protrude into a flow channel, which is marked by arrows 18.
  • This flow channel 18 is bounded at least in the area above the rotor blades 16 radially outwardly by an insert wall 20.
  • the insert wall 20 extends on the one hand axially limited the gas inlet region radially outwards, then passes into a contour of the blades adapted area and finally forms with an approximately radially extending region an outer boundary wall of the flow channel 18 in
  • the compressor diffuser 22 has guide vanes 40 and is connected by means of a screw 23 on the one hand to the insert wall 20 on the other hand with a compressor housing 24 surrounding the compressor wheel 14.
  • the compressor housing 14 has an outer housing part 26 and an inner wall 28.
  • the inner wall 28 connects directly to the radially extending portion of the insert wall 20 and radially outwardly surrounds the axially extending portion of the insert wall 20.
  • the compressor housing 24 is gas inlet side by means of a compound 30, which is designed here in the form of a screw connection, connected to an upstream component 32.
  • This upstream component 32 may be, for example, an intake manifold or a filter damper.
  • the compressor wheel 14 acts as a wedge between the compressor diffuser 22 and the insert wall 20.
  • the resulting large axial forces are transmitted in this radial compressor 12 through the insert wall 20 on the inner wall 28 and further on the connection 30. If the axial forces are too great, the connection 30 will not withstand the sudden load and the upstream component 32 as well as the inner wall 28 and the insert wall 20 will be ejected axially.
  • turbocharger with radial compressor according to the invention of which a part of the compressor side is shown analogously to the illustration in FIG. 1 in FIG. 2, this can not happen.
  • the radial compressor 12 with the compressor wheel 14, the rotor blades 16, the insert wall 20, the compressor diffuser 22 and the compressor housing 24, 26, 28 together with the upstream component 32 is basically the same, as shown in the turbocharger of the prior art in Fig. 1st
  • the turbocharger according to the invention for the centrifugal compressor 12 has a burst protection device 34 which prevents the housing parts 28, the insert wall 20 and upstream components 32 from being thrown off axially.
  • the burst protection device 34 includes the insert wall 20 which defines the flow channel 18 radially outwardly beyond the rotor blades 16 of the compressor wheel 14, wherein the Insert wall has a predetermined breaking point 36.
  • This predetermined breaking point 36 is arranged in the example shown in FIG. 2 in the region 38 between the axially and the radially extending portion of the insert wall 20, between the blades 16 of the compressor wheel 14 and the guide vanes 40 of the compressor diffuser 22.
  • the inner wall 28 has in its adjoining the radially extending portion of the insert wall 20 part an initial radius Ra on which is about as large or slightly larger than the radius Re of the insert wall 20 in the region of the predetermined breaking point 36.
  • FIG. 3 shows a further embodiment of the burst-prevention device 34 according to the invention, in which a plurality of the radially tapered sections 44, 46 are formed as brake lugs 50 protruding radially inward from the inner wall 28.
  • the predetermined breaking point 36 may also be located elsewhere in the area above the blades, between the axially and radially extending portion of the insert wall 20, or even in the upstream portion of the radially extending portion of the insert wall 20. If not too great axial forces are expected, it is possible to provide only the predetermined breaking point 36 in the insert wall 20.
  • the conical slopes of the inner wall may be approximately in the range between 5 ° and 30 ° for the first section 42 and approximately in the range between 5 ° and 50 ° in the further sections 44, 46.
  • Brake elements 48 and brake lugs 50 are preferably formed integrally with the insert wall 20 and with the inner wall 28, as shown in FIGS. 2 and 3. But they can also be designed as separate components.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
EP02719599A 2001-05-04 2002-04-30 Berstschutzvorrichtung für radialverdichter von turboladern Expired - Lifetime EP1383987B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH816012001 2001-05-04
CH8162001 2001-05-04
PCT/CH2002/000238 WO2002090722A1 (de) 2001-05-04 2002-04-30 Berstschutzvorrichtung für radialverdichter von turboladern

Publications (2)

Publication Number Publication Date
EP1383987A1 EP1383987A1 (de) 2004-01-28
EP1383987B1 true EP1383987B1 (de) 2006-01-04

Family

ID=4538978

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02719599A Expired - Lifetime EP1383987B1 (de) 2001-05-04 2002-04-30 Berstschutzvorrichtung für radialverdichter von turboladern

Country Status (7)

Country Link
EP (1) EP1383987B1 (ko)
JP (1) JP4088161B2 (ko)
KR (1) KR100865650B1 (ko)
CN (1) CN1328482C (ko)
DE (1) DE50205516D1 (ko)
TW (1) TW576886B (ko)
WO (1) WO2002090722A1 (ko)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10844726B2 (en) 2017-10-23 2020-11-24 MTU Aero Engines AG Blade and rotor for a turbomachine and turbomachine
WO2023086776A1 (en) * 2021-11-11 2023-05-19 Progress Rail Locomotive Inc. Compressor housing

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1586745B1 (de) 2004-04-13 2015-07-29 ABB Turbo Systems AG Verdichtergehäuse
DE102004027594B4 (de) * 2004-06-05 2006-06-29 Man B & W Diesel Ag Strömungsmaschine mit radial durchströmtem Verdichterrad
EP1719879B1 (de) * 2005-05-03 2008-01-30 ABB Turbo Systems AG Berstschutzvorrichtung für Radialverdichter
DE102005039820B4 (de) 2005-08-22 2007-06-28 Man Diesel Se Containment-Sicherung für Strömungsmaschinen mit radial durchströmtem Verdichterrad
JP2010501770A (ja) * 2006-08-24 2010-01-21 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 フィルター・マフラーの取付け装置
WO2008055717A1 (de) * 2006-11-10 2008-05-15 Abb Turbo Systems Ag Gehäuseverbindung eines abgasturboladers
US7871243B2 (en) * 2007-06-05 2011-01-18 Honeywell International Inc. Augmented vaneless diffuser containment
DE102007055615A1 (de) * 2007-11-20 2009-05-28 Mann + Hummel Gmbh Gehäuse für einen Radialverdichter
EP2212561B1 (de) * 2007-11-20 2011-10-19 Mann + Hummel GmbH Gehäuse für einen radialverdichter
EP2090755A1 (de) * 2008-02-14 2009-08-19 ABB Turbo Systems AG Turboladergehäuse
EP2216516A1 (de) 2009-02-04 2010-08-11 ABB Turbo Systems AG Berstschutzvorrichtung für Radialverdichter
JP5476816B2 (ja) * 2009-06-26 2014-04-23 株式会社Ｉｈｉ 遠心圧縮機及びターボチャージャ
DE102010027762B4 (de) * 2010-04-15 2015-06-25 Man Diesel & Turbo Se Einsatzstück für eine Strömungsmaschine und damit ausgerüstete Strömungsmaschine
DE102011017419B4 (de) * 2010-04-19 2021-11-18 GM Global Technology Operations LLC (n. d. Ges. d. Staates Delaware) Ablenkeinheit für eine Gasströmung in einem Kompressor und Kompressor, der diese enthält
DE102010064025A1 (de) 2010-12-23 2012-06-28 Abb Turbo Systems Ag Berstschutz
DE102011010673A1 (de) * 2011-02-08 2012-08-09 Voith Patent Gmbh Gehäuse für einen Abgasturbolader oder ein Turbocompound-System
GB2499627A (en) * 2012-02-23 2013-08-28 Napier Turbochargers Ltd Turbocharger casing
DE102013107134A1 (de) * 2013-07-05 2015-01-08 Abb Turbo Systems Ag Lufteintritt eines Verdichters eines Abgasturboladers
DE102013109222A1 (de) * 2013-08-26 2015-02-26 Abb Turbo Systems Ag Vorrichtung für einen Turbolader
ITCO20130067A1 (it) 2013-12-17 2015-06-18 Nuovo Pignone Srl Girante con elementi di protezione e compressore centrifugo
JP6133439B2 (ja) * 2013-12-24 2017-05-24 三菱重工業株式会社 圧縮機および過給機
WO2015098175A1 (ja) * 2013-12-27 2015-07-02 三菱重工業株式会社 コンプレッサ
GB201404050D0 (en) * 2014-03-07 2014-04-23 Cummins Ltd A turbine
JP6404082B2 (ja) * 2014-10-28 2018-10-10 三菱重工業株式会社 遠心圧縮機およびそれを備えた過給機
DE102015014030A1 (de) * 2015-10-31 2017-05-04 Man Diesel & Turbo Se Abgasturbolader und Stützstruktur für einen Abgasturbolader
DE102015014550A1 (de) * 2015-11-11 2017-05-11 Man Diesel & Turbo Se Ansaugsystem für einen Abgasturbolader und Abgasturbolader
DE102016111081B4 (de) * 2016-06-17 2024-08-01 Man Energy Solutions Se Strömungsmaschine
JP2018132045A (ja) * 2017-02-17 2018-08-23 三菱重工業株式会社 回転機械
DE102018102704A1 (de) * 2018-02-07 2019-08-08 Man Energy Solutions Se Radialverdichter
DE102018129128A1 (de) * 2018-11-20 2020-05-20 Man Energy Solutions Se Einsatzstück für einen Turbolader
US11519423B1 (en) * 2021-11-11 2022-12-06 Progress Rail Locomotive Inc. Compressor joint

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10844726B2 (en) 2017-10-23 2020-11-24 MTU Aero Engines AG Blade and rotor for a turbomachine and turbomachine
WO2023086776A1 (en) * 2021-11-11 2023-05-19 Progress Rail Locomotive Inc. Compressor housing
US11719129B2 (en) 2021-11-11 2023-08-08 Progress Rail Locomotive Inc. Compressor housing

Also Published As

Publication number Publication date
EP1383987A1 (de) 2004-01-28
KR100865650B1 (ko) 2008-10-29
KR20030092128A (ko) 2003-12-03
DE50205516D1 (de) 2006-03-30
JP2004525297A (ja) 2004-08-19
TW576886B (en) 2004-02-21
WO2002090722A1 (de) 2002-11-14
JP4088161B2 (ja) 2008-05-21
CN1328482C (zh) 2007-07-25
CN1537193A (zh) 2004-10-13

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