EP1260677A2 - Turbine axiale avec protection contre des éclatements - Google Patents

Turbine axiale avec protection contre des éclatements Download PDF

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Publication number
EP1260677A2
EP1260677A2 EP02010986A EP02010986A EP1260677A2 EP 1260677 A2 EP1260677 A2 EP 1260677A2 EP 02010986 A EP02010986 A EP 02010986A EP 02010986 A EP02010986 A EP 02010986A EP 1260677 A2 EP1260677 A2 EP 1260677A2
Authority
EP
European Patent Office
Prior art keywords
turbine
exhaust gas
housing
axial
gas diffuser
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.)
Granted
Application number
EP02010986A
Other languages
German (de)
English (en)
Other versions
EP1260677A3 (fr
EP1260677B1 (fr
EP1260677B2 (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
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
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=7685942&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1260677(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
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
Publication of EP1260677B2 publication Critical patent/EP1260677B2/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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 with one a turbine inflow housing with a gas outlet side wall and a Turbine outflow housing formed with a gas inlet side wall Turbine housing, in this a turbine disk supported by a shaft Blades is arranged, the turbine disk to the outside of one Exhaust gas diffuser is limited to form a flow channel and at A burst protection in the turbine housing in the axial area of the turbine disk is provided.
  • burst protection was in the form of a Burst protection ring as an integral part of the turbine outflow housing or a cover ring for the turbine disc, for example by means of a Clamping ring is screwed to the diffuser, a sufficient means to to prevent broken blades from escaping from the turbine housing.
  • At least the cover ring is therefore not made of one brittle material such as steel or a steel alloy, while the other parts of the axial turbine continue in a known manner from cast parts can exist so that this energy dissipation is optimized. Also for same purpose is preferably the cover ring on the support wall supported by means of flexible connecting elements on the exhaust gas diffuser.
  • the fragments meet the annular one radially outward Extension piece of the outer contour of the exhaust gas diffuser.
  • This ring-shaped, or cylindrical extension piece in that it over the axial Area of the turbine disk is designed, a substantial part of the Absorb kinetic energy of the fragments.
  • the ring-shaped extension piece of the outer contour of the exhaust gas diffuser by means of radially arranged ribs reinforced.
  • the remaining energy of the fragments is replaced by that in radial Direction exactly above the center plane of the turbine disc gas inlet side wall of the turbine discharge housing, wherein a massive flange connection between the turbine inflow housing, Diffuser outer wall and turbine outflow housing is preferably rigid.
  • the exhaust gas turbocharger of the type on which the drawing is based comprises one Axial turbine 1, which consists of a turbine inflow housing 2 with a gas outlet side wall 3 and a turbine outflow housing 4 with a gas inlet side wall 5 has assembled turbine housing.
  • a turbine disk 7 carried by a shaft 6 Blades 8 arranged.
  • the blades 8 of the turbine disc 7 are outward from one Exhaust gas diffuser 9 limited and by this in a flow channel 14 added.
  • the outer wall 10 of the exhaust gas duffus 9 is in the axial area the turbine disk 7 in the radial direction with an outer 11 and one Inner contour 12 executed. Between the outer 11 and inner contour 12 is one cylindrical or annular support wall 13 formed, the Outer contour 11 in the form of an annular or cylindrical Extension piece is executed, which over the axial area of Turbine disk 7 is designed pulled.
  • the Flow channel 14 formed, the exhaust gases of a not shown here Motors picks up and in a known manner to the blades 8 of the Turbine disk 7 continues.
  • Upstream in the flow channel 14 is a one Outer 15 and an inner ring 16 comprising nozzle ring inserted by means of Connecting elements 17 and flanges 18 on outer 15 and inner ring 16 with the turbine inflow housing 2 is connected.
  • Axially between the nozzle ring 15, 16 and exhaust gas diffuser 9 is a cover ring 19 for the Blades 8 of the turbine disc 7, the flow channel 14 on the Inner contour 12 of the exhaust gas diffuser 9 clamped in a sealing manner, such that the Nozzle ring both between its outer ring 15 and cover ring 19 a gap 28 as well as a gap between its inner ring 16 and the turbine disk 7 20 trains.
  • Another gap 21 is between the turbine disk 7 and the Leave inner wall 22 of exhaust gas diffuser 9 in a known manner.
  • the cover ring 19 is located on the support wall 13 of the exhaust gas diffuser 9 supporting by means of flexible connecting elements 27, for example expansion screws, on Exhaust diffuser 9 fixed.
  • the turbine inflow 2 and turbine outflow housing 4 are in this way with one another connected that the gas inlet side wall 5 of the turbine outflow housing 4 in radial direction exactly aligned over the central plane 23 of the turbine disk 7 stands.
  • the annular extension piece of the outer contour 11 of the exhaust gas diffuser 9 has a peripheral, or several individual mounting flange / s at the end 24 on, which in the connection of turbine inflows 2 and Turbine outflow housing 4 clamped and by means of rigid connecting elements 25 is screwed to these.
  • annular extension piece of the outer contour 11 is by means of radially arranged ribs 26 reinforced.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
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 true EP1260677A2 (fr) 2002-11-27
EP1260677A3 EP1260677A3 (fr) 2005-02-09
EP1260677B1 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109057877A (zh) * 2018-10-26 2018-12-21 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

Families Citing this family (12)

* 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
WO2008023068A2 (fr) * 2006-08-24 2008-02-28 Abb Turbo Systems Ag boîtier de turbine
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
DE102018127719A1 (de) * 2018-11-07 2020-05-07 Man Energy Solutions Se Kompensationsvorrichtung zur Kompensation thermischer Relativbewegungen

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4648790A (en) * 1983-06-29 1987-03-10 Bbc Brown, Boveri & Company, Limited Axial turbine for exhaust gas turbochargers
EP0806547A1 (fr) * 1996-05-08 1997-11-12 Asea Brown Boveri AG Turbine axiale pour turbocompresseurs

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6049523A (en) * 1997-05-30 2000-04-11 Lucent Technologies Inc. System and method for achieving efficient coordination of protection switching

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4648790A (en) * 1983-06-29 1987-03-10 Bbc Brown, Boveri & Company, Limited Axial turbine for exhaust gas turbochargers
EP0806547A1 (fr) * 1996-05-08 1997-11-12 Asea Brown Boveri AG Turbine axiale pour turbocompresseurs

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109057877A (zh) * 2018-10-26 2018-12-21 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
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

Also Published As

Publication number Publication date
DE50207358D1 (de) 2006-08-10
DE10125250C5 (de) 2007-03-29
EP1260677A3 (fr) 2005-02-09
EP1260677B1 (fr) 2006-06-28
JP4153722B2 (ja) 2008-09-24
DE10125250C1 (de) 2002-09-12
EP1260677B2 (fr) 2016-11-02
JP2003003804A (ja) 2003-01-08

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