EP1260677B1 - Turbine axiale avec protection contre des éclatements - Google Patents

Turbine axiale avec protection contre des éclatements Download PDF

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Publication number
EP1260677B1
EP1260677B1 EP02010986A EP02010986A EP1260677B1 EP 1260677 B1 EP1260677 B1 EP 1260677B1 EP 02010986 A EP02010986 A EP 02010986A EP 02010986 A EP02010986 A EP 02010986A EP 1260677 B1 EP1260677 B1 EP 1260677B1
Authority
EP
European Patent Office
Prior art keywords
turbine
housing
axial
exhaust gas
disk
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
EP02010986A
Other languages
German (de)
English (en)
Other versions
EP1260677A3 (fr
EP1260677B2 (fr
EP1260677A2 (fr
Inventor
Klaus Dr. Bartholomä
Wolfgang Schmidt
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.)
MAN Energy Solutions SE
Original Assignee
MAN B&W Diesel GmbH
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Filing date
Publication date
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Application filed by MAN B&W Diesel GmbH filed Critical MAN B&W Diesel GmbH
Publication of EP1260677A2 publication Critical patent/EP1260677A2/fr
Publication of EP1260677A3 publication Critical patent/EP1260677A3/fr
Publication of EP1260677B1 publication Critical patent/EP1260677B1/fr
Application granted granted Critical
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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 an axial turbine of an exhaust gas turbocharger having a turbine housing formed by a turbine inlet housing with a gas outlet side wall and a Turbinenabströmgephaseuse with a gas inlet side wall, in which a supported by a shaft turbine disk is arranged with blades, the turbine disk to the outside of a Abgasdiffusor to form a flow channel is limited and in which a burst protection is provided in the turbine housing in the axial region of the turbine disk.
  • EP 0 806 547 A1 describes a generic axial-flow turbine in which the gas inlet-side wall of the turbine exhaust housing assumes the function of bursting protection for the turbine disk.
  • the burst protection as a ring in the form of an integral, substantially radially extending component of the gas inlet side wall of Turbinenabströmgephaseuses formed and connected either directly or via an upstream axial extension piece with the Turbinenzuströmgephaseuse.
  • burst protection in the form of a burst protection ring as an integral part of the turbine exhaust casing or cover ring for the turbine disk, which is bolted to the diffuser, for example by means of a clamping ring, was sufficient means to prevent broken blades from exiting the turbine casing.
  • an axial turbine of the type mentioned with simple and inexpensive means so educate that the escape of fragments of a ruptured turbine disk or a ruptured impeller can be prevented from the turbine housing, even at extremely high peripheral speeds, without to provide an additional burst protection outside of the turbine housing.
  • the outer wall of the exhaust diffuser is designed in the axial region of the turbine disk in the radial direction with an outer and an inner contour and between the outer and inner contour of an annular support wall is provided, wherein the outer contour is designed in the form of an annular extension piece that over the axial area of the turbine disk is configured such that a turbine ring cover ring is provided between the support wall and the inner contour of the exhaust gas diffuser, and turbine inlet and turbine exhaust casings are connected such that the gas inlet side wall of the turbine exhaust housing is radially above the center plane of the turbine disk stands, a three-stage bursting protection is achieved in the axial turbine, which meets all requirements.
  • the fragments are first (1st stage) thrown against the cover ring on the support wall of the exhaust diffuser. If the fragments are so large that the cover ring and the supporting wall do not withstand the stresses, then part of the kinetic energy of the fragments is dissipated by their breakage.
  • At least the cover ring is therefore made of a non-brittle material such as steel or a steel alloy, while the other parts of the axial turbine may continue to consist of castings in a known manner, so that this energy dissipation is optimized.
  • the cover ring is preferably fixed to the support wall supporting means of flexible connecting elements on the exhaust diffuser.
  • the fragments meet radially outward on the annular extension piece of the outer contour of the exhaust diffuser.
  • This annular or cylindrical extension piece in that it is designed to be pulled over the axial region of the turbine disk, can absorb a substantial part of the kinetic energy of the fragments.
  • the annular extension piece of the outer contour of the exhaust gas diffuser is preferably reinforced by means of radially arranged ribs.
  • the residual energy of the fragments is absorbed by the gas inlet side wall of the turbine exhaust housing, which is located in the radial direction just above the center plane of the turbine disk, wherein a solid flange connection between Turbinenzuströmgeophuse, diffuser outer wall and Turbinenabströmgephaseuse is preferably rigid.
  • the exhaust gas turbocharger of the type on which the drawing is based comprises an axial turbine 1, which has a turbine inlet housing 2 with a gas outlet side wall 3 and a turbine exhaust housing 4 with a turbine inlet housing 2 gas inlet side wall 5 has a composite turbine housing.
  • a turbine inlet housing 2 with a gas outlet side wall 3
  • a turbine exhaust housing 4 with a turbine inlet housing 2 gas inlet side wall 5 has a composite turbine housing.
  • a composite turbine housing In the turbine housing a supported by a shaft 6 turbine disk 7 with blades 8 is arranged.
  • the rotor blades 8 of the turbine disk 7 are bounded on the outside by an exhaust gas diffuser 9 and are received by it in a flow channel 14.
  • the outer wall 10 of the exhaust gas diffuser 9 is designed in the axial region of the turbine disk 7 in the radial direction with an outer 11 and an inner contour 12.
  • a cylindrical or annular support wall 13 is formed, wherein the outer contour 11 is designed in the form of an annular or cylindrical extension piece, which is designed to be pulled over the axial region of the turbine disk 7.
  • the flow channel 14 is formed, which receives the exhaust gases of a motor not shown here and continues in a known manner to the blades 8 of the turbine disk 7.
  • Upstream in the flow channel 14 is an outer 15 and an inner ring 16 comprehensive nozzle ring inserted, which is connected by means of connecting elements 17 and flanges 18 on outer 15 and inner ring 16 with the Turbinenzuströmgephaseuse 2.
  • Axially between the nozzle ring 15, 16 and the exhaust diffuser 9 is a cover 19 for the blades 8 of the turbine disk 7 sealingly clamped the flow channel 14 on the inner contour 12 of the exhaust diffuser 9, such that the nozzle ring both between its outer ring 15 and cover 19 a gap 28 as well between its inner ring 16 and the turbine disk 7 forms a gap 20.
  • Another gap 21 is left between the turbine disk 7 and the inner wall 22 of the exhaust gas diffuser 9 in a known manner.
  • the cover ring 19 is fixed to the support wall 13 of the exhaust gas diffuser 9 by means of flexible connecting elements 27, for example. Expansion screws, fixed to the exhaust gas diffuser 9.
  • Turbinenzuström- 2 and Turbinenabströmgenosuse 4 are connected to each other such that the gas inlet side wall 5 of the Turbinenabströmgenosuses 4 in the radial direction is exactly aligned above the center plane 23 of the turbine disk 7.
  • the annular extension piece of the outer contour 11 of the exhaust gas diffuser 9 has at its end a circumferential, or several individual fastening flange / s 24, which is clamped in the connection of Turbinenzuström- 2 and Turbinenabströmgephaseuse 4 and screwed by means of rigid connecting elements 25 with these.
  • annular extension piece of the outer contour 11 is reinforced by means of radially arranged ribs 26.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Claims (6)

  1. Turbine axiale (1) d'un turbocompresseur d'échappement comportant un boîtier de turbine constitué d'un boîtier amont (2) muni d'une paroi (3) côté sortie des gaz et d'un boîtier aval (4) muni d'une paroi (5) côté entrée des gaz, un disque (7) supporté par un arbre (6) et muni de pales (8) est placé dans ce boîtier, le disque (7) étant limité vers l'extérieur par un diffuseur d'échappement (9) en formant un canal d'écoulement (14) et une protection contre l'éclatement est prévue dans le boîtier dans la zone axiale du disque (7), la paroi extérieure (10) du diffuseur d'échappement (9) comporte un contour extérieur (11) et un contour intérieur (12) dans la zone axiale du disque (7) et en direction radiale et le boîtier amont (2) et le boîtier aval (4) sont reliés l'un à l'autre de telle manière que la paroi côté entrée des gaz (5) du boîtier aval (4) en direction radiale se trouve sur le plan médian (23) du disque (7),
    caractérisée en ce qu'
    une paroi d'appui annulaire (13) est prévue entre le contour extérieur (11) et le contour intérieur (12), le contour extérieur (11) ayant la forme d'une pièce ajoutée annulaire qui s'étend sur la zone axiale du disque, et
    une bague de recouvrement (19) placée entre la paroi d'appui (13) et le contour intérieur (12) du diffuseur d'échappement (9) est prévue pour le disque (7) et les pales (8).
  2. Turbine axiale selon la revendication 1,
    caractérisée en ce que
    la bague extérieure (19) est fixée au diffuseur d'échappement (9) à l'aide d'éléments de liaison (27) flexibles en s'appuyant contre la paroi d'appui (13).
  3. Turbine axiale selon la revendication 1,
    caractérisée en ce que
    la pièce ajoutée annulaire du contour extérieur (11) du diffuseur d'échappement (9) est renforcée à l'aide de nervures (26) radiales.
  4. Turbine axiale selon la revendication 1 ou 3,
    caractérisée en ce que
    la pièce ajoutée annulaire du contour extérieur (11) comporte à son extrémité une collerette de fixation (24) qui peut être serrée dans la liaison entre le boîtier amont (2) et le boîtier aval (4).
  5. Turbine axiale selon la revendication 1 ou 4,
    caractérisée en ce que
    la liaison entre le boîtier amont (2) et le boîtier aval (4) a lieu à l'aide d'éléments de liaison (25) rigides.
  6. Turbine axiale selon la revendication 1,
    caractérisée en ce qu'
    au moins la bague de recouvrement (19) du diffuseur d'échappement (9) est fabriquée en un matériau non cassant comme l'acier ou un alliage d'acier.
EP02010986.4A 2001-05-23 2002-05-17 Turbine axiale avec protection contre des éclatements Expired - Lifetime EP1260677B2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10125250 2001-05-23
DE2001125250 DE10125250C5 (de) 2001-05-23 2001-05-23 Axialturbine eines Abgastruboladers mit internem Berstschutz

Publications (4)

Publication Number Publication Date
EP1260677A2 EP1260677A2 (fr) 2002-11-27
EP1260677A3 EP1260677A3 (fr) 2005-02-09
EP1260677B1 true EP1260677B1 (fr) 2006-06-28
EP1260677B2 EP1260677B2 (fr) 2016-11-02

Family

ID=7685942

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02010986.4A Expired - Lifetime EP1260677B2 (fr) 2001-05-23 2002-05-17 Turbine axiale avec protection contre des éclatements

Country Status (3)

Country Link
EP (1) EP1260677B2 (fr)
JP (1) JP4153722B2 (fr)
DE (2) DE10125250C5 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006039064B4 (de) 2006-08-19 2020-06-25 Man Energy Solutions Se Abgasturbolader für eine Brennkraftmaschine
KR101055231B1 (ko) * 2006-08-24 2011-08-09 에이비비 터보 시스템즈 아게 터빈 하우징
DE102008061398A1 (de) 2008-12-10 2010-06-17 Man Diesel Se Berstschutz für eine Strömungsmaschine
JP4905565B2 (ja) * 2010-02-04 2012-03-28 トヨタ自動車株式会社 ターボチャージャおよびそのホイールハウジング
JP5889266B2 (ja) 2013-11-14 2016-03-22 三菱重工業株式会社 タービン
DE202014002980U1 (de) 2014-04-08 2014-04-16 Man Diesel & Turbo Se Axialturbine für einen Abgasturbolader
DE202014002981U1 (de) 2014-04-08 2014-04-16 Man Diesel & Turbo Se Axialturbine für einen Abgasturbolader
CN104454146A (zh) * 2014-10-27 2015-03-25 中国北车集团大连机车研究所有限公司 涡轮增压器轴流涡轮断裂的防护装置
CN106368740B (zh) * 2016-11-14 2017-12-05 沈阳航空航天大学 一种燃气轮机涡轮的双层壁外环结构
DE102017120543A1 (de) 2017-09-06 2019-03-07 Man Diesel & Turbo Se Axialturbine eines Turboladers und Turbolader
DE102018105827A1 (de) * 2018-03-14 2019-09-19 Man Energy Solutions Se Verschalung eines Turboladers und Turbolader
CN109057877B (zh) * 2018-10-26 2023-11-28 中国船舶重工集团公司第七0三研究所 一种氦气涡轮机用涡轮静子结构
DE102018127719A1 (de) * 2018-11-07 2020-05-07 Man Energy Solutions Se Kompensationsvorrichtung zur Kompensation thermischer Relativbewegungen

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0131736B1 (fr) * 1983-06-29 1987-01-21 BBC Brown Boveri AG Turbine axiale pour un turbocompresseur
DE19618313B4 (de) * 1996-05-08 2005-07-21 Abb Turbo Systems Ag Axialturbine eines Abgasturboladers
US6049523A (en) * 1997-05-30 2000-04-11 Lucent Technologies Inc. System and method for achieving efficient coordination of protection switching

Also Published As

Publication number Publication date
EP1260677A3 (fr) 2005-02-09
DE50207358D1 (de) 2006-08-10
DE10125250C1 (de) 2002-09-12
JP4153722B2 (ja) 2008-09-24
JP2003003804A (ja) 2003-01-08
EP1260677B2 (fr) 2016-11-02
EP1260677A2 (fr) 2002-11-27
DE10125250C5 (de) 2007-03-29

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