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EP0856639A2 - Anneau de guidage pour une turbine radiale - Google Patents

Anneau de guidage pour une turbine radiale Download PDF

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Publication number
EP0856639A2
EP0856639A2 EP98810023A EP98810023A EP0856639A2 EP 0856639 A2 EP0856639 A2 EP 0856639A2 EP 98810023 A EP98810023 A EP 98810023A EP 98810023 A EP98810023 A EP 98810023A EP 0856639 A2 EP0856639 A2 EP 0856639A2
Authority
EP
European Patent Office
Prior art keywords
turbine
exhaust gas
housing
seal
nozzle ring
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.)
Withdrawn
Application number
EP98810023A
Other languages
German (de)
English (en)
Other versions
EP0856639A3 (fr
Inventor
Marcel Meier
Martin Seiler
Claus Weisheit
Marcel Zehnder
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
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Turbo Systems AG
Publication of EP0856639A2 publication Critical patent/EP0856639A2/fr
Publication of EP0856639A3 publication Critical patent/EP0856639A3/fr
Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/048—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial admission
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • 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 the exhaust gas turbine of a turbocharger, with one in the inflow duct arranged the exhaust gas turbine, the working medium on the turbine blades conductive nozzle ring.
  • the nozzle rings of the exhaust gas turbines of turbochargers are changed by Operating conditions, i.e. Increase or decrease in pressure and temperature of the working medium, highly stressed. Depending on the used Turbine and according to the specific conditions of use, the working medium have a large temperature gradient. Because a nozzle ring opposite the turbine components surrounding it always have a low mass possesses, it is subject to relatively strong temperature expansions.
  • the nozzle ring is often attached by simply jamming it in the Exhaust turbine housing. Since the nozzle ring does not change accordingly in this case can expand, material warping and cracks occur, so that such a nozzle ring does not have a sufficient lifespan. So he has to be exchanged in relatively short time intervals, which in addition to additional Cost also results in a loss of turbine work.
  • the invention tries to avoid all of these disadvantages. You have the task to create a nozzle ring for the exhaust gas turbine of a turbocharger, which in addition to an improved service life also a constant efficiency guaranteed.
  • a radial expansion gap is formed between the turbine housing and the nozzle ring and at least in this expansion gap a seal is arranged.
  • the nozzle ring consists of two in the recess arranged fasteners, which over a number are connected to each other by guide vanes. Either in at least one of the Fasteners or in at least one of the fasteners surrounding components of the turbine housing is a seal receiving circumferential groove formed.
  • the seal is designed as a lamellar ring.
  • One out of one is particularly advantageous sufficient heat-resistant material, such as chrome nickel steel existing double lamellar ring.
  • Such a seal encloses you 720 ° angle. It can not only withstand high temperatures of up to 750 ° C Resist undamaged but also provides an improved seal of the expansion gap. This can further increase turbine efficiency and the service life of the nozzle ring can also be increased.
  • the seal is also made of a sufficiently heat-resistant Made of existing piston ring material. This is another possibility given to seal the expansion gap, which according to the concrete operating conditions is available.
  • an embodiment of the invention is based on a Radial turbine of a turbocharger shown.
  • the exhaust gas turbocharger mainly consists of a compressor, not shown and an exhaust gas turbine designed as a radial turbine 1.
  • the radial turbine 1 has a turbine housing 2, with a spiral gas inlet housing 3, a gas outlet housing 4 designed as a gas outlet flange and a Intermediate wall, turbine-side housing component 5.
  • a turbine wheel 7 In the turbine housing 2 is a turbine wheel 7 with rotor blades carried by a shaft 6 8 rotatably mounted. There is also no compressor on shaft 6 shown compressor wheel arranged.
  • the gas inlet housing 3 goes downstream into an inflow duct 9 for the exhaust gases 10 a connected to the exhaust gas turbocharger, also not shown Internal combustion engine over.
  • a nozzle ring 11 is form-fitting in the inflow channel 9 between the gas inlet housing 3 and the gas outlet flange 4 and the intermediate wall 5 arranged.
  • the shaft 6 is by means of bearings 12 in a bearing housing 13 rotatably mounted.
  • the gas inlet housing 3 and the bearing housing 13 are connected to one another via a tensioning band 14 arranged in the circumferential direction.
  • the gas outlet flange 4 and the gas inlet housing 3 are by screws 15 releasably attached to each other (Fig. 1).
  • the nozzle ring 11 consists of two annular fastening elements 16, 17, which are connected to one another via a number of guide vanes 18.
  • the turbine housing 2 for Receiving the nozzle ring 11 has the turbine housing 2 in the region of the transition from the gas inlet housing 3 to the gas outlet flange 4 or to the intermediate wall 5 a recess 19.
  • a radial expansion gap 20 is formed, which is both the axial and the radial expansion of the nozzle ring 11 allowed.
  • Gas inlet side of the nozzle ring 11 is in the fastener 17 a circumferential groove 21 is arranged and in the flow direction of the exhaust gases 10 aligned.
  • the groove 21 takes a double lamellar ring, i.e. seal 22 enclosing an angle of 720 °.
  • the double slat ring 22 is made of chrome-nickel steel, although of course other heat-resistant ones Materials can be used.
  • Both in the groove 21 and in the recess 19 of the turbine housing 2 is a sealing surface 23, 24 for each Double lamellar ring 22 arranged (Fig. 2).
  • a simple one or a triple slat ring can be used.
  • Figure 3 is a longitudinal section through the indicated in Figure and also only partially shown double lamellar ring 22 shown. For the sake of clarity an enlarged view was chosen.
  • exhaust gases 10 first enter the spiral Gas inlet housing 3 of the radial turbine 1. Be in the gas inlet housing 3 it accelerates and via the nozzle ring 11 with an optimal flow angle passed to the turbine wheel 7. There the exhaust gases 10 are finally expanded. They give a power, which drives the shaft 6 and so that the compressor wheel serves.
  • the nozzle ring can 11 Expand freely in both the axial and radial directions. Doing so the exhaust gas pressure acting via the inflow duct 9 and the expansion gap 20 the double lamellar ring 22 always on the sealing surface 23 of the groove 21. Accordingly an extensive sealing of the expansion gap 20 is achieved. At Corresponding test bench tests were able to achieve efficiency gains of up to three points compared to variants without sealing the expansion gap 20 be determined.
  • the circumferential groove 21 is in the Gas outlet flange 4 formed (Fig. 4).
  • This is a second variant of the arrangement given the seal 22, which with appropriate design requirements is used.
  • a second sealing surface 23 arranged in the groove 21 Sealing surface 27 is formed on the fastening element 17 of the nozzle ring 11.
  • the function of this double lamellar ring 22 is analogous to the first exemplary embodiment.
  • the circumferential groove 21 can also be in the fastening element 16 or in the partition 5, i.e. also gas inlet or gas outlet side of the Nozzle ring 11 are formed (not shown).
  • a piston ring is designed in a third exemplary embodiment Seal 28 on the gas inlet side of the nozzle ring 11, between its fastening element 17 and the gas inlet housing 3.
  • the piston ring 28 is received by a correspondingly adapted groove 29.
  • a sealing surface 30, 31 for the piston ring 28 is arranged.
  • To ensure a good seal To ensure a piston ring 28 is used with a hooked impact (not shown). All other components of the radial turbine 1 are analogous to the first Embodiment formed.
  • the function of the piston ring 28 corresponds the function of the double lamellar ring 22.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP98810023A 1997-01-29 1998-01-20 Anneau de guidage pour une turbine radiale Withdrawn EP0856639A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19703033A DE19703033A1 (de) 1997-01-29 1997-01-29 Abgasturbine eines Turboladers
DE19703033 1997-01-29

Publications (2)

Publication Number Publication Date
EP0856639A2 true EP0856639A2 (fr) 1998-08-05
EP0856639A3 EP0856639A3 (fr) 2000-04-19

Family

ID=7818574

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810023A Withdrawn EP0856639A3 (fr) 1997-01-29 1998-01-20 Anneau de guidage pour une turbine radiale

Country Status (7)

Country Link
US (1) US5964574A (fr)
EP (1) EP0856639A3 (fr)
JP (1) JP3004616B2 (fr)
KR (1) KR19980070758A (fr)
CN (1) CN1192513A (fr)
CZ (1) CZ292035B6 (fr)
DE (1) DE19703033A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7384236B2 (en) 2002-12-02 2008-06-10 Abb Turbo Systems Ag Exhaust-gas-turbine casing
EP3929407A1 (fr) * 2020-06-23 2021-12-29 ABB Schweiz AG Bague de tuyère modulaire pour une étage de turbine d'une turbomachine

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US6565468B2 (en) 1999-12-21 2003-05-20 The Gates Corporation Tensioner with damping mechanism
JP4370662B2 (ja) * 2000-03-17 2009-11-25 アイシン精機株式会社 可変容量ターボチャージャ
US6287091B1 (en) * 2000-05-10 2001-09-11 General Motors Corporation Turbocharger with nozzle ring coupling
EP1180632A1 (fr) * 2000-08-07 2002-02-20 ABB Turbo Systems AG Système de verrouillage axial
DE10051223A1 (de) 2000-10-16 2002-04-25 Alstom Switzerland Ltd Verbindbare Statorelemente
JP2003184563A (ja) * 2001-12-14 2003-07-03 Aisin Seiki Co Ltd 可変容量ターボチャージャ
EP1394363B1 (fr) * 2002-08-26 2006-03-01 BorgWarner Inc. Système d'aubes de guidage variables pour une turbine
EP1536103B1 (fr) 2003-11-28 2013-09-04 BorgWarner, Inc. Turbomachine avec aubes de guidage et agencement de fixation
JP4729901B2 (ja) * 2004-11-01 2011-07-20 株式会社Ｉｈｉ 過給機および密封装置
US8047772B2 (en) * 2005-03-30 2011-11-01 Honeywell International Inc. Variable geometry turbine for a turbocharger and method of controlling the turbine
KR20090039770A (ko) * 2006-08-18 2009-04-22 가부시키가이샤 아이에이치아이 전동 과급기
US7559199B2 (en) 2006-09-22 2009-07-14 Honeywell International Inc. Variable-nozzle cartridge for a turbocharger
JP5045304B2 (ja) * 2007-08-16 2012-10-10 株式会社Ｉｈｉ ターボチャージャ
JP4952558B2 (ja) * 2007-12-12 2012-06-13 株式会社Ｉｈｉ ターボチャージャ
JP2009197633A (ja) * 2008-02-20 2009-09-03 Ihi Corp ターボチャージャ
DE102008057878A1 (de) * 2008-11-18 2010-05-20 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
JP5402061B2 (ja) * 2009-02-17 2014-01-29 株式会社Ｉｈｉ ターボチャージャ
JP5402682B2 (ja) * 2010-01-29 2014-01-29 株式会社Ｉｈｉ ターボチャージャのシール装置
US8857178B2 (en) * 2011-06-28 2014-10-14 Caterpillar Inc. Nozzled turbocharger turbine and associated engine and method
WO2013048687A1 (fr) * 2011-09-27 2013-04-04 Borgwarner Inc. Support semi-perméable tenant de façon étanche un arbre d'actionnement
JP5710452B2 (ja) * 2011-11-16 2015-04-30 トヨタ自動車株式会社 ターボチャージャ
CN104246170B (zh) * 2012-03-30 2018-09-21 博格华纳公司 带有集成隔热屏的涡轮增压器轴承壳体
JP5949164B2 (ja) * 2012-05-29 2016-07-06 株式会社Ihi 可変ノズルユニット及び可変容量型過給機
JP6051791B2 (ja) * 2012-11-06 2016-12-27 トヨタ自動車株式会社 ターボチャージャ
EP2733311B1 (fr) * 2012-11-16 2019-01-02 ABB Turbo Systems AG Couronne directrice
JP6331423B2 (ja) * 2014-01-29 2018-05-30 株式会社Ihi 可変容量型過給機
US10465601B2 (en) * 2014-10-02 2019-11-05 Ihi Corporation Variable nozzle unit and variable-capacity supercharger
CN104564174B (zh) * 2014-12-29 2017-01-18 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机透平静叶弹性密封结构
US9890788B2 (en) 2015-03-09 2018-02-13 Caterpillar Inc. Turbocharger and method
US10066639B2 (en) 2015-03-09 2018-09-04 Caterpillar Inc. Compressor assembly having a vaneless space
US9903225B2 (en) 2015-03-09 2018-02-27 Caterpillar Inc. Turbocharger with low carbon steel shaft
US9752536B2 (en) 2015-03-09 2017-09-05 Caterpillar Inc. Turbocharger and method
US9810238B2 (en) 2015-03-09 2017-11-07 Caterpillar Inc. Turbocharger with turbine shroud
US9732633B2 (en) 2015-03-09 2017-08-15 Caterpillar Inc. Turbocharger turbine assembly
US9683520B2 (en) 2015-03-09 2017-06-20 Caterpillar Inc. Turbocharger and method
US9915172B2 (en) 2015-03-09 2018-03-13 Caterpillar Inc. Turbocharger with bearing piloted compressor wheel
US9822700B2 (en) 2015-03-09 2017-11-21 Caterpillar Inc. Turbocharger with oil containment arrangement
US9739238B2 (en) 2015-03-09 2017-08-22 Caterpillar Inc. Turbocharger and method
US9638138B2 (en) 2015-03-09 2017-05-02 Caterpillar Inc. Turbocharger and method
US10006341B2 (en) 2015-03-09 2018-06-26 Caterpillar Inc. Compressor assembly having a diffuser ring with tabs
US9879594B2 (en) 2015-03-09 2018-01-30 Caterpillar Inc. Turbocharger turbine nozzle and containment structure
US9777747B2 (en) 2015-03-09 2017-10-03 Caterpillar Inc. Turbocharger with dual-use mounting holes
US9650913B2 (en) 2015-03-09 2017-05-16 Caterpillar Inc. Turbocharger turbine containment structure
CN106337697B (zh) * 2016-09-13 2019-02-01 中国北方发动机研究所(天津) 一种喷嘴环密封结构
US10731546B2 (en) * 2017-02-06 2020-08-04 Borgwarner Inc. Diffuser in wastegate turbine housings
DE102017114397A1 (de) * 2017-06-28 2019-01-03 2G Energy AG Verfahren zur Anpassung eines Turboladers sowie eines Stationärmotorsystems sowie Turbolader und Stationärmotorsystem
US11231047B2 (en) * 2017-08-28 2022-01-25 Kabushiki Kaisha Toyota Jidoshokki Turbocharger
DE102017127628A1 (de) * 2017-11-22 2019-05-23 Man Energy Solutions Se Turbine und Turbolader
US10612418B2 (en) * 2018-03-22 2020-04-07 GM Global Technology Operations LLC Nested flange joint
KR20240161676A (ko) * 2022-03-22 2024-11-12 터보 시스템즈 스위츠랜드 엘티디. 레이디얼 터빈용 노즐 링, 배기 터빈, 및 터보차저
CN119053772A (zh) * 2022-05-25 2024-11-29 株式会社Ihi 涡轮机以及增压器
DE102022118731A1 (de) 2022-07-26 2024-02-01 Rolls-Royce Solutions GmbH Turbinenanordnungen, Turbolader und Brennkraftmaschine

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7384236B2 (en) 2002-12-02 2008-06-10 Abb Turbo Systems Ag Exhaust-gas-turbine casing
US7946809B2 (en) 2002-12-02 2011-05-24 Abb Turbo Systems Ag Exhaust-gas-turbine casing
EP3929407A1 (fr) * 2020-06-23 2021-12-29 ABB Schweiz AG Bague de tuyère modulaire pour une étage de turbine d'une turbomachine
WO2021259862A1 (fr) * 2020-06-23 2021-12-30 Abb Switzerland Ltd. Couronne directrice modulaire pour un étage de turbine d'une turbomachine

Also Published As

Publication number Publication date
CN1192513A (zh) 1998-09-09
JPH10220235A (ja) 1998-08-18
KR19980070758A (ko) 1998-10-26
DE19703033A1 (de) 1998-07-30
CZ26398A3 (cs) 1998-08-12
US5964574A (en) 1999-10-12
JP3004616B2 (ja) 2000-01-31
EP0856639A3 (fr) 2000-04-19
CZ292035B6 (cs) 2003-07-16

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