EP2054587A2 - Boîtier de turbine - Google Patents

Boîtier de turbine

Info

Publication number
EP2054587A2
EP2054587A2 EP07802890A EP07802890A EP2054587A2 EP 2054587 A2 EP2054587 A2 EP 2054587A2 EP 07802890 A EP07802890 A EP 07802890A EP 07802890 A EP07802890 A EP 07802890A EP 2054587 A2 EP2054587 A2 EP 2054587A2
Authority
EP
European Patent Office
Prior art keywords
housing
diffuser
insert
gas outlet
turbine
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
EP07802890A
Other languages
German (de)
English (en)
Other versions
EP2054587B1 (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=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2054587(A2) "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

Links

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 and a method for producing such a turbine housing.
  • 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.
  • Gas outlet housing of axial turbines such as known from DE 101 37 899 C1 are usually formed as a collecting space, which has on one side in an approximately semicircular cross section, and on the opposite side a round or rectangular flange for connection to a discharge line includes.
  • the diffuser Into the collecting space projects into 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 outflow housings only in the region of the diffuser due to precisely tuned Diffusorgeomethen. 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 a section through the outflow of an axial turbine with inventively integrated diffuser and gas outlet housing
  • FIG. 2 shows an enlarged section of an exchangeable insert piece, which is arranged in the region radially outside the turbine blades in the diffuser.
  • Fig. 1 shows the outflow region 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 diffuser
  • the insert 15 can be fastened between the diffuser outer wall and, for example, the nozzle ring 4 or the gas inlet housing 2.
  • the insert can be attached to any housing piece, for example by means of screws.
  • Fig. 2 it is indicated how for different lengths blades with correspondingly 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 by the adjacent housing pieces with respect
  • Turbine axis remains centered. This can advantageously be achieved by providing a centering seat at the end of the insert 16 at the end of the insert. 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.
  • Insert be provided before installation in the integrated housing with the desired inner diameter, which is due to the selected
  • Turbine blade lengths results. 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)

Abstract

L'invention consiste à améliorer avec des moyens simples les conditions d'écoulement dans la zone de sortie d'une turbine axiale, en configurant sur une turbine axiale la partie d'écoulement du boîtier qui va du diffuseur au boîtier de sortie de gaz sous la forme d'un composant qui présente la combinaison d'un canal intérieur et d'un canal extérieur d'écoulement. L'intégration du diffuseur dans le boîtier de sortie de gaz permet d'obtenir un boîtier optimisé en termes aérodynamiques et qui assure un ralentissement maximum de l'écoulement tout en minimisant les pertes de charge.
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
EP06405365 2006-08-24
EP06405366 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 true EP2054587A2 (fr) 2009-05-06
EP2054587B1 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)

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
DE102019101602A1 (de) * 2019-01-23 2020-07-23 Man Energy Solutions Se Strömungsmaschine
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2008023068A3 *

Also Published As

Publication number Publication date
EP2054587B1 (fr) 2009-12-02
KR20090035599A (ko) 2009-04-09
WO2008023068A2 (fr) 2008-02-28
JP2010501774A (ja) 2010-01-21
CN101506476A (zh) 2009-08-12
WO2008023068A3 (fr) 2008-06-19
KR101055231B1 (ko) 2011-08-09
CN101506476B (zh) 2011-09-14
DE502007002221D1 (de) 2010-01-14

Similar Documents

Publication Publication Date Title
EP2054587B1 (fr) Boîtier de turbine
DE112015001237B4 (de) Abgasturbolader
DE60011400T2 (de) Verdichterabblasung durch ununterbrochenen ringförmigen spalt
WO2007121843A1 (fr) Turbocompresseur avec géométrie de turbine réglable et ouverture d'équilibrage de la pression dans la bague porte-pales
EP3682092B1 (fr) Turbine à gaz d'échappement avec diffuseur
EP2617941B1 (fr) Dispositif de conduite d'air ainsi que procédé de fabrication d'un dispositif de conduite d'air, rotor et turbomachine
EP2685054B1 (fr) Diffuseur d'une turbine de gaz d'échappement
EP3121371A1 (fr) Turbine comprenant des aubes directrices refroidies
EP2617947B1 (fr) Turbine à gaz d'avion avec soufflante ajustable
CH705324A1 (de) Axialverdichter mit einer Einspritzvorrichtung zum Eindüsen einer Flüssigkeit.
EP3495639B1 (fr) Module de compresseur pour une turbomachine réduisant la couche limite dans un carter intermédiaire de compresseur
EP2821596A1 (fr) Admission d'air d'un compresseur d'un turbocompresseur à gaz d'échappement
EP3921577B1 (fr) Système de chambre de combustion à tubes et installation de turbine à gaz pourvue d'un tel système de chambre de combustion à tubes
EP3921576B1 (fr) Résonateur, procédé de fabrication d'un résonateur de ce type, et ensemble brûleur pourvu d'un résonateur de ce type
EP3737850B1 (fr) Filtre-amortisseur de bruit pour un turbocompresseur d'un moteur à combustion interne
EP3601739B1 (fr) Turbocompresseur pour un moteur à combustion interne ainsi que roue de turbine
DE102010040823A1 (de) Turbolader
EP2722495A1 (fr) Carter d'entrée de gaz et turbine associée pour gaz d'échappement
DE10220507B4 (de) Verbrennungsmotor
DE102004033884A1 (de) Abgasturbolader für eine Brennkraftmaschine
DE10352252B4 (de) Kompressor für eine Turbogruppe
DE102012109549B4 (de) Verstellbarer Leitapparat für einen Abgasführungsabschnitt einer Turbine, und Abgasturbolader
WO2020152143A1 (fr) Sous-ensemble pour une alimentation en air d'un moteur à combustion interne et conduit d'alimentation en air d'un moteur à combustion interne le comprenant
EP2042707A1 (fr) Turbine à gaz stationnaire pour génération d'énergie
EP3940203A1 (fr) Turbine de gaz d'échappement

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20090217

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

17Q First examination report despatched

Effective date: 20090604

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

DAX Request for extension of the european patent (deleted)
RBV Designated contracting states (corrected)

Designated state(s): DE GB

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 502007002221

Country of ref document: DE

Date of ref document: 20100114

Kind code of ref document: P

PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

26 Opposition filed

Opponent name: TOGNUM AG

Effective date: 20100812

PLAX Notice of opposition and request to file observation + time limit sent

Free format text: ORIGINAL CODE: EPIDOSNOBS2

PLAF Information modified related to communication of a notice of opposition and request to file observations + time limit

Free format text: ORIGINAL CODE: EPIDOSCOBS2

PLBB Reply of patent proprietor to notice(s) of opposition received

Free format text: ORIGINAL CODE: EPIDOSNOBS3

RDAF Communication despatched that patent is revoked

Free format text: ORIGINAL CODE: EPIDOSNREV1

APBM Appeal reference recorded

Free format text: ORIGINAL CODE: EPIDOSNREFNO

APBP Date of receipt of notice of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA2O

APAH Appeal reference modified

Free format text: ORIGINAL CODE: EPIDOSCREFNO

APBQ Date of receipt of statement of grounds of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA3O

PLAB Opposition data, opponent's data or that of the opponent's representative modified

Free format text: ORIGINAL CODE: 0009299OPPO

PLAB Opposition data, opponent's data or that of the opponent's representative modified

Free format text: ORIGINAL CODE: 0009299OPPO

R26 Opposition filed (corrected)

Opponent name: TOGNUM AG

Effective date: 20100812

R26 Opposition filed (corrected)

Opponent name: ROLLS-ROYCE POWER SYSTEMS AG

Effective date: 20100812

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20170822

Year of fee payment: 11

Ref country code: DE

Payment date: 20170822

Year of fee payment: 11

REG Reference to a national code

Ref country code: DE

Ref legal event code: R064

Ref document number: 502007002221

Country of ref document: DE

Ref country code: DE

Ref legal event code: R103

Ref document number: 502007002221

Country of ref document: DE

APBU Appeal procedure closed

Free format text: ORIGINAL CODE: EPIDOSNNOA9O

RDAG Patent revoked

Free format text: ORIGINAL CODE: 0009271

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: PATENT REVOKED

27W Patent revoked

Effective date: 20171127

GBPR Gb: patent revoked under art. 102 of the ep convention designating the uk as contracting state

Effective date: 20171127