EP0131736B1 - Turbine axiale pour un turbocompresseur - Google Patents

Turbine axiale pour un turbocompresseur Download PDF

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Publication number
EP0131736B1
EP0131736B1 EP84106485A EP84106485A EP0131736B1 EP 0131736 B1 EP0131736 B1 EP 0131736B1 EP 84106485 A EP84106485 A EP 84106485A EP 84106485 A EP84106485 A EP 84106485A EP 0131736 B1 EP0131736 B1 EP 0131736B1
Authority
EP
European Patent Office
Prior art keywords
turbine
deflection
duct
exhaust gas
axial
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
Application number
EP84106485A
Other languages
German (de)
English (en)
Other versions
EP0131736A1 (fr
Inventor
Hansulrich Dr. Dipl. Ing. Hörler
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0131736A1 publication Critical patent/EP0131736A1/fr
Application granted granted Critical
Publication of EP0131736B1 publication Critical patent/EP0131736B1/fr
Expired 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/045—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type the wheel comprising two adjacent bladed wheel portions, e.g. with interengaging blades for damping vibrations
    • 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 for exhaust gas turbochargers.
  • the inner wall of the gas deflection channel arranged between the turbine guide apparatus and the turbine blades is rigid and immovable.
  • a swirl loss occurs due to the gas friction on this wall. Due to the high peripheral speed of the gas, which increases radially inwards, this inner wall of the gas deflection channel causes relatively high friction losses.
  • the isentropic efficiency of the turbine drops additively by about 2% to 5%.
  • the invention is therefore based on the object of creating an axial turbine in which the swirl loss in the gas deflecting duct is reduced to a minimum, and good efficiency is thereby achieved.
  • Fig. 1 denotes the turbocharger axis.
  • the axial turbine shown with radial gas inflow is connected via the turbine housing 7 to an exhaust line, not shown, of a supercharged diesel engine.
  • the turbocharger shaft 2 is supported in the turbine housing 7 by means of shaft bearings 10 and carries a turbine disk 3 provided with the turbine blades 4.
  • turbine guide blades 5 Upstream of the turbine rotor blades 4 through which gas flows axially, turbine guide blades 5 through which radial flow flows are arranged in the annular deflection channel 7a.
  • a sealing air duct 8 and an air discharge duct 9 are arranged in the turbine housing 7.
  • the inner wall of the rotationally symmetrical exhaust gas deflecting duct 7b is designed as a deflecting collar 6 rotating with the turbocharger shaft 2.
  • This deflecting collar 6 is rigidly connected to the turbocharger shaft 2 by means of screws 12.
  • the outside diameter of the rotating deflection collar 6 is larger than the diameter of the turbine disk 3 and can at most be the same as the outside diameter of the turbine rotor.
  • An element for the contactless sealing of the exhaust gas deflection channel is provided between the rotating deflection collar 6 and the housing 7.
  • This element consists of two labyrinth seals 11, 11 ', which are arranged on a cylindrical, concentric, inwardly open surface of the deflecting collar 6.
  • a sealing air channel 8 arranged in the turbine housing 7 is connected to a radial gap 15 arranged between the labyrinth seal 11 ′ facing the turbine and the labyrinth seal 11 facing away from the turbine.
  • An air discharge duct 9 arranged in the turbine housing 7 is connected to an air space 13.
  • the engine exhaust gas flows through the exhaust duct 7a, through the ring of the guide vanes 5 and the exhaust gas deflecting duct 7b to the turbine rotor blades 4, in which it relaxes with the output of power and is then expelled into the atmosphere through an exhaust line, not shown.
  • the predominantly radially flowing engine exhaust gas is accelerated tangentially on the turbine guide vanes 5. This creates a swirl acting in the direction of rotation of the turbine.
  • the sealing air supply through the sealing air duct 8 serves to cool the turbocharger shaft 2 and the turbine disk 3 and prevents the exhaust gas from flowing out of the exhaust gas deflection duct 7b through the air space 13 to the shaft bearing 10 and to the environment.
  • the element for contactless sealing of the deflection channel 7b consists of a labyrinth seal 11 concentrically arranged in a plane normal to the axis.
  • the labyrinth seal 11 is arranged on the outside diameter of the rotating deflection collar 6.
  • the small amount of exhaust gas flowing inwards from the exhaust gas deflection duct 7b through the labyrinth seal 11 is discharged into the discharge duct 9 with the sealing air coming radially from the inside out.
  • the sealing air consumption in this version is smaller than that in the versions without a rotating deflecting collar 6. This sealing air consumption is mainly determined by the necessary cooling of the deflecting collar.
  • a very small amount of the engine exhaust gas is lost here through the labyrinth seal 11. This loss of volume is also negligible due to the low gas density.
  • a main advantage of this design is that the axial force on the turbocharger shaft is practically eliminated.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (5)

1. Turbine axiale pour turbocompresseur de suralimentation à gaz d'échappement, se composant essentiellement d'une roue de turbine (3) montée sur l'arbre (2) du turbocompresseur et garnie d'aubes mobiles (4) de turbine parcourues axialement, et d'un corps de turbine (7) dans lequel l'arbre (2) du turbocompresseur est supporté, dans laquelle une couronne d'aubes directrices (5) de turbine parcourues radialement est disposée dans le corps de turbine (7) en amont des aubes mobiles (4) et dans laquelle un canal (7b) de déviation des gaz, présentant une symétrie de rotation, est disposé entre les aubes directrices (5) de la turbine et les aubes mobiles (4) de la turbine, et dans laquelle la paroi intérieure du canal (7b) de déviation des gaz d'échappement, qui présente une symétrie de rotation, est constituée par une collerette de déviation (6) non garnie d'aubes, assemblée rigidement à l'arbre (2) du turbocompresseur et tournant avec lui.
2. Turbine axiale suivant la revendication 1, caractérisée en ce que le diamètre extérieur de la collerette de déviation (6) est plus grand que le diamètre de la roue de turbine (3) et est au maximum égal au diamètre extérieur du rotor de la turbine.
3. Turbine axiale suivant la revendication 1, caractérisée en ce qu'entre la collerette de déviation (6) rotative et le corps de turbine (7), il est prévu un élément destiné à obturer sans contact le canal (7b) de déviation des gaz d'échappement.
4. Turbine axiale suivant la revendication 3, caractérisée en ce que l'élément destiné à obturer sans contact le canal (7b) de déviation se compose de deux joints à labyrinthe (11, 11') montés sur une surface cylindrique, concentrique et ouverte vers l'intérieur, de la collerette de déviation (6), en ce qu'un canal (8) d'air de balayage ménagé dans le corps de turbine (7) est raccordé à une fente radiale (15) située entre le joint à labyrinthe (.11') proche de la turbine et le joint à labyrinthe (11) plus éloigné de la turbine, ce qui permet d'introduire l'air de balayage radialement vers l'intérieur à travers la fente radiale (15) et d'évacuer l'air de balayage à travers le joint à labyrinthe (11), éloigné de la turbine, jusqu'au rayon extérieur de la collerette de déviation (6) dans le canal des gaz (7b) avant la turbine et à travers le joint à labyrinthe (11'), proche de la turbine, dans l'atmosphère ou dans le canal d'évacuation des gaz.
5. Turbine axiale suivant la revendication 3, caractérisée en ce que l'élément destiné à obturer sans contact le canal (7b) de déviation est constitué d'un joint à labyrinthe (11) disposé concentriquement dans un plan normal à l'axe, ce qui permet d'évacuer les gaz d'échappement du moteur provenant du canal (7b) de déviation des gaz d'échappement en même temps que l'air de balayage venant radialement de l'intérieur, vers un canal (9) d'évacuation des gaz.
EP84106485A 1983-06-29 1984-06-06 Turbine axiale pour un turbocompresseur Expired EP0131736B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH3559/83 1983-06-29
CH355983 1983-06-29

Publications (2)

Publication Number Publication Date
EP0131736A1 EP0131736A1 (fr) 1985-01-23
EP0131736B1 true EP0131736B1 (fr) 1987-01-21

Family

ID=4258600

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84106485A Expired EP0131736B1 (fr) 1983-06-29 1984-06-06 Turbine axiale pour un turbocompresseur

Country Status (6)

Country Link
US (1) US4648790A (fr)
EP (1) EP0131736B1 (fr)
JP (1) JPS6013926A (fr)
KR (1) KR910003258B1 (fr)
DE (1) DE3462169D1 (fr)
DK (1) DK314684A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105745431A (zh) * 2013-11-07 2016-07-06 株式会社京浜 调压阀

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2648042B2 (ja) * 1991-05-31 1997-08-27 ジューキ株式会社 ボタン供給装置
DE19618313B4 (de) * 1996-05-08 2005-07-21 Abb Turbo Systems Ag Axialturbine eines Abgasturboladers
DE10051223A1 (de) 2000-10-16 2002-04-25 Alstom Switzerland Ltd Verbindbare Statorelemente
DE10125250C5 (de) * 2001-05-23 2007-03-29 Man Diesel Se Axialturbine eines Abgastruboladers mit internem Berstschutz
BR0117061B1 (pt) * 2001-06-26 2009-12-01 aparelho de turbina de exaustão.
US6715766B2 (en) * 2001-10-30 2004-04-06 General Electric Company Steam feed hole for retractable packing segments in rotary machines
GB2440344A (en) * 2006-07-26 2008-01-30 Christopher Freeman Impulse turbine design
GB0814764D0 (en) 2008-08-13 2008-09-17 Cummins Turbo Tech Ltd Engine braking method and system
US8453445B2 (en) * 2010-04-19 2013-06-04 Honeywell International Inc. Axial turbine with parallel flow compressor
US8468826B2 (en) * 2010-04-19 2013-06-25 Honeywell International Inc. Axial turbine wheel
US8453448B2 (en) * 2010-04-19 2013-06-04 Honeywell International Inc. Axial turbine
US8353161B2 (en) * 2010-04-19 2013-01-15 Honeywell International Inc. High diffusion turbine wheel with hub bulb
JP6030462B2 (ja) * 2013-01-30 2016-11-24 株式会社Ihi 加圧焼却設備及び加圧焼却方法
JP6017033B2 (ja) * 2013-06-20 2016-10-26 三菱重工業株式会社 半径流入式軸流タービン及びターボチャージャ
US20150159660A1 (en) * 2013-12-06 2015-06-11 Honeywell International Inc. Axial turbine with radial vnt vanes
DE102014200916A1 (de) * 2014-01-20 2015-07-23 Ford Global Technologies, Llc Brennkraftmaschine mit zweiflutiger Axialturbine und gruppierten Zylindern
DE102015223257A1 (de) 2015-11-25 2017-06-01 Volkswagen Aktiengesellschaft Abgasturbine, Abgasturbolader, Brennkraftmaschine und Kraftfahrzeug
DE102016207698A1 (de) * 2016-05-04 2017-11-09 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
JP6674913B2 (ja) * 2017-01-16 2020-04-01 三菱重工業株式会社 半径流入式タービン、過給機及び過給機の組み立て方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0093462A1 (fr) * 1982-04-29 1983-11-09 BBC Brown Boveri AG Turbocompresseur avec une valve annulaire glissante

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1358070A (en) * 1916-02-23 1920-11-09 Allis Chalmers Mfg Co Hydraulic installation
US1803220A (en) * 1929-07-24 1931-04-28 Thompson Thomas Water turbine
CH330608A (de) * 1953-09-11 1958-06-15 Garrett Corp Laufschaufelrad für elastische Strömungsmittel
US2781999A (en) * 1954-09-24 1957-02-19 Siemens Ag Turbine construction
US2854212A (en) * 1955-07-19 1958-09-30 Siemens Ag Turbine apparatus
GB978080A (en) * 1961-04-06 1964-12-16 Gasturbinenbau Und Energiemasc Improvements in rotors for gas turbines and compressors
CH480543A (de) * 1967-08-18 1969-10-31 Sulzer Ag Anlage zum Fördern, Verdichten bzw. Umwälzen von Gasen mit einem durch einen Elektromotor angetriebenen Fördergebläse
US3859008A (en) * 1971-07-06 1975-01-07 Andritz Ag Maschf Pump with offset inflow and discharge chambers
US3832090A (en) * 1972-12-01 1974-08-27 Avco Corp Air cooling of turbine blades
SU966316A1 (ru) * 1980-12-23 1982-10-15 Ордена Ленина И Ордена Трудового Красного Знамени Производственное Объединение "Невский Завод" Им.В.И.Ленина Корпус центробежного нагнетател
SU964197A1 (ru) * 1981-03-11 1982-10-07 Ленинградский Ордена Ленина Политехнический Институт Им.М.И.Калинина Проточна часть паровой турбины

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0093462A1 (fr) * 1982-04-29 1983-11-09 BBC Brown Boveri AG Turbocompresseur avec une valve annulaire glissante

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105745431A (zh) * 2013-11-07 2016-07-06 株式会社京浜 调压阀

Also Published As

Publication number Publication date
JPH052817B2 (fr) 1993-01-13
EP0131736A1 (fr) 1985-01-23
KR850000589A (ko) 1985-02-28
JPS6013926A (ja) 1985-01-24
US4648790A (en) 1987-03-10
DK314684A (da) 1984-12-30
KR910003258B1 (ko) 1991-05-25
DK314684D0 (da) 1984-06-27
DE3462169D1 (en) 1987-02-26

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