EP2054587B1 - Boîtier de turbine - Google Patents

Boîtier de turbine Download PDF

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Publication number
EP2054587B1
EP2054587B1 EP07802890A EP07802890A EP2054587B1 EP 2054587 B1 EP2054587 B1 EP 2054587B1 EP 07802890 A EP07802890 A EP 07802890A EP 07802890 A EP07802890 A EP 07802890A EP 2054587 B1 EP2054587 B1 EP 2054587B1
Authority
EP
European Patent Office
Prior art keywords
casing
diffuser
insert
turbine
housing
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.)
Revoked
Application number
EP07802890A
Other languages
German (de)
English (en)
Other versions
EP2054587A2 (fr
Inventor
Matthias Jarusel
Marco Di Pietro
Markus Städeli
Peter Neuenschwander
Bent Phillipsen
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=38740249&utm_source=***_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2054587(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Priority to EP07802890A priority Critical patent/EP2054587B1/fr
Publication of EP2054587A2 publication Critical patent/EP2054587A2/fr
Application granted granted Critical
Publication of EP2054587B1 publication Critical patent/EP2054587B1/fr
Revoked legal-status Critical Current
Anticipated expiration legal-status 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • 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
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • 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
    • F05D2250/70—Shape

Definitions

  • the invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines.
  • It relates to the housing of an axial turbine of an exhaust gas turbocharger.
  • Exhaust gas turbochargers are used to increase the performance of internal combustion engines, in particular reciprocating engines.
  • an exhaust gas turbocharger usually has a centrifugal compressor and a radial or axial turbine.
  • the turbine side is configured according to the requirements of the internal combustion engine.
  • turbine blades with different blade heights can be provided, for example, for a given turbine size, that is to say a specific turbine wheel size and a corresponding turbine housing.
  • shorter or longer blades are mounted on the blade carrier.
  • turbine blades with deviating blade height are to be retrofitted into an existing exhaust gas turbine later.
  • the housing parts in the immediate vicinity of the rotor blades that is to say in particular the outer wall of the diffuser, must also be adapted. This can be cumbersome in conventional exhaust gas turbines, especially when larger housing parts, which may have a considerable weight, must be replaced on an exhaust gas turbocharger.
  • Gas outlet housing of axial turbines such as out DE 101 37 899 C1
  • they are designed as a collecting space which has an approximately semicircular cross-section on one side and a round or rectangular flange for connection to an outflow line on the opposite side.
  • the diffuser which extends virtually axially following the blade ring of the turbine wheel and undergoes a radial deflection in the region of the mouth into the collecting space.
  • the flow is controlled in conventional Abströmgephaseen only in the region of the diffuser due to precisely matched diffuser geometries. When the flow leaves the diffuser into the plenum, the flow goes its uncontrolled course.
  • the object of the invention is to improve the outflow of an axial turbine with simple means fluidically.
  • the housing in the outflow region, from the diffuser to the gas outlet housing is designed as a component with a combined inner and outer flow channel.
  • the integration of the diffuser in the gas outlet housing a housing is created, which is aerodynamically optimized and ensures maximum flow delay with minimal pressure loss.
  • the combined inner and outer flow channel is delimited by the gas outlet housing and a diffuser wall, wherein the point of intersection between the gas outlet housing and the diffuser wall according to the invention is along the circumference at different radii. This results in two, varying in the circumferential direction partial flow channels, which are responsible for the desired flow optimization.
  • the diffuser has a replaceable insert in the area radially outside the rotor blades, which can be exchanged for another insert with other geometric dimensions as needed and depending on the selected turbine blade height.
  • Fig. 1 shows the outflow area of an axial turbine.
  • the housing 1 in the outflow region essentially comprises the turbine-near diffuser, which is delimited by an inner diffuser wall 12 and an outer diffuser wall 11, and the outer gas outlet housing 10, which accommodates the inner flow 13 emerging from the inner region of the diffuser and as an outer flow 14 leads to the outlet flange of the gas outlet housing.
  • the task of the housing in the outflow area of the turbine is to delay the flow velocity of the exhaust gas without losing much pressure.
  • the gas outlet housing 10 is integrally formed with the diffuser housing. This results in an aerodynamically optimal transition from the inner flow region 13 to the outer flow region 14.
  • the region of the intersection between the gas outlet housing 10 and the outer wall 11 of the diffuser is T-shaped. The point of intersection T travels along the circumference of the diffuser wall, so that the outer flow channel has an unequal cross-section.
  • the gas outlet housing with integrated diffuser optionally contains an insert piece 15, which is arranged in the region radially outside the turbine blades 3.
  • Fig. 2 shows this area in an enlarged view. If a new blade height is provided in an axial turbine with a given housing size, ie a given integrated diffuser and gas outlet housing, the insert 15 can be exchanged to compensate for the distance between the blade tips and the housing. This can be easily, and especially without great logistical and assembly-technical effort to realize several turbine configurations with one and the same turbine size.
  • the differing housing parts are only the small inserts. It does not need to be replaced large diffusers or even replaced whole gas outlet housing.
  • the insert 15 can be, as in the Fig. 2 , shown secured between the diffuser outer wall and, for example, the nozzle ring 4 or the gas inlet housing 2. Alternatively, the insert can be attached to any housing piece, for example by means of screws. In Fig. 2 is indicated how for different lengths blades with appropriately offset blade tips 32, the inner contour of the different inserts is moved radially inward.
  • the outer fastening ring of the nozzle ring 4 is arranged upstream of the insert 15 in the flow direction.
  • the inner diameter of the outer mounting ring of the nozzle ring is smaller than the inner diameter of the inner contour of the insert 15. The difference is advantageously 0.3 to 3 times the distance between the blade tips and the inner contour of the insert.
  • the insert may optionally be arranged between two housing parts such that it has a certain range of motion in the radial direction. Thus, thermal stresses in the insert can be prevented. It should be noted that the insert remains centered by the adjacent housing pieces with respect to the turbine axis. This can advantageously be achieved by providing a centering seat at the exit end of the insert 16. Radially outside the turbine blades, the insert can expand freely in the radial direction, provided that a gap 17 is provided between the insert and the radially outside the insert piece arranged housing part.
  • the wall thickness of the insert is small compared to the adjacent housing parts. As a result, thermal tensions can be prevented during rapid temperature changes. Further, the difference in the thermal expansion of the insert and the turbine runner can be kept small.
  • the transition between insert 15 and the outer diffuser wall 11 may be formed flat or provided with a positive or negative step.
  • the insert may be provided prior to installation in the integrated housing with the desired inner diameter, which results from the selected turbine blade lengths. If the blade length has to be adjusted during operation, the insert piece can be correspondingly replaced by another insert piece, which has a larger or smaller inner diameter. For a given turbine size, all insert pieces have the same outside mass, only the inside diameter varies.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (4)

  1. Boîtier d'une turbine axiale, comprenant un diffuseur et un boîtier de sortie de gaz, dans lequel le diffuseur pénètre dans un espace collecteur limité par le boîtier d'entrée de gaz, caractérisé en ce que le diffuseur et le boîtier de sortie de gaz sont réalisés sous forme de partie de boîtier d'une seule pièce intégrée.
  2. Boîtier selon la revendication 1, dans lequel le boîtier de sortie de gaz (10) vient en contact avec la paroi du diffuseur (11) au niveau d'un point d'intersection (T) et la position du point d'intersection (T) sur la paroi du diffuseur varie dans la direction périphérique.
  3. Boîtier selon l'une quelconque des revendications 1 ou 2, dans lequel le boîtier intégré comprend, dans une région radialement à l'extérieur des aubes mobiles (31) de la turbine axiale une pièce d'insertion (15) qui est insérée sous forme de composant séparé dans le boîtier intégré.
  4. Boîtier selon la revendication 3, dans lequel, entre la pièce d'insertion (15) et la partie de boîtier disposée radialement à l'extérieur est prévue une fente radiale (17) et la pièce d'insertion (15) présente, à l'extrémité du côté de la sortie de gaz (16), un siège de centrage, par le biais duquel elle est centrée sur la partie de boîtier disposée radialement à l'extérieur.
EP07802890A 2006-08-24 2007-08-24 Boîtier de turbine Revoked EP2054587B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07802890A EP2054587B1 (fr) 2006-08-24 2007-08-24 Boîtier de turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP06405366 2006-08-24
EP06405365 2006-08-24
PCT/EP2007/058849 WO2008023068A2 (fr) 2006-08-24 2007-08-24 boîtier de turbine
EP07802890A EP2054587B1 (fr) 2006-08-24 2007-08-24 Boîtier de turbine

Publications (2)

Publication Number Publication Date
EP2054587A2 EP2054587A2 (fr) 2009-05-06
EP2054587B1 true EP2054587B1 (fr) 2009-12-02

Family

ID=38740249

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07802890A Revoked EP2054587B1 (fr) 2006-08-24 2007-08-24 Boîtier de turbine

Country Status (6)

Country Link
EP (1) EP2054587B1 (fr)
JP (1) JP2010501774A (fr)
KR (1) KR101055231B1 (fr)
CN (1) CN101506476B (fr)
DE (1) DE502007002221D1 (fr)
WO (1) WO2008023068A2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019101602A1 (de) * 2019-01-23 2020-07-23 Man Energy Solutions Se Strömungsmaschine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2685054B1 (fr) * 2012-07-09 2020-11-25 ABB Schweiz AG Diffuseur d'une turbine de gaz d'échappement
JP5889266B2 (ja) * 2013-11-14 2016-03-22 三菱重工業株式会社 タービン
JP6731359B2 (ja) * 2017-02-14 2020-07-29 三菱日立パワーシステムズ株式会社 排気ケーシング、及びこれを備える蒸気タービン
DE102017124467A1 (de) * 2017-10-19 2019-04-25 Abb Turbo Systems Ag Diffusoranordnung einer Abgasturbine
CN109098780B (zh) * 2018-05-24 2024-05-14 中车大连机车研究所有限公司 一种涡轮增压器燃气废气进排气壳体
SE543851C2 (en) * 2019-12-12 2021-08-10 Scania Cv Ab Exhaust additive dosing system comprising a turbocharger
CN112524383B (zh) * 2020-11-17 2022-04-19 中国航发四川燃气涡轮研究院 用于航空发动机涡轮部件试验器的轴向膨胀自补偿装置

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB815475A (en) * 1954-09-10 1959-06-24 Henschel & Sohn Ges Mit Beschr Improvements in gas turbines with a small built-in heat exchanger
DD267079A1 (de) 1987-12-23 1989-04-19 Bergmann Borsig Veb Austrittsgehaeuse mit radialem austritt fuer stroemungsmaschinen
JP3547522B2 (ja) * 1995-05-17 2004-07-28 新潟原動機株式会社 排気タービン過給機の洗浄装置
US6168375B1 (en) * 1998-10-01 2001-01-02 Alliedsignal Inc. Spring-loaded vaned diffuser
DE10125250C5 (de) * 2001-05-23 2007-03-29 Man Diesel Se Axialturbine eines Abgastruboladers mit internem Berstschutz
DE10137899C1 (de) * 2001-08-02 2003-04-03 Man B & W Diesel Ag Strömungsmaschine
EP1574681A1 (fr) * 2004-03-11 2005-09-14 Ford Global Technologies, LLC Turbine à gaz avec diffuseur d'échappement

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019101602A1 (de) * 2019-01-23 2020-07-23 Man Energy Solutions Se Strömungsmaschine

Also Published As

Publication number Publication date
CN101506476A (zh) 2009-08-12
KR20090035599A (ko) 2009-04-09
WO2008023068A3 (fr) 2008-06-19
EP2054587A2 (fr) 2009-05-06
DE502007002221D1 (de) 2010-01-14
WO2008023068A2 (fr) 2008-02-28
JP2010501774A (ja) 2010-01-21
KR101055231B1 (ko) 2011-08-09
CN101506476B (zh) 2011-09-14

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