EP0999349A2 - Turbine axiale - Google Patents

Turbine axiale Download PDF

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Publication number
EP0999349A2
EP0999349A2 EP99810971A EP99810971A EP0999349A2 EP 0999349 A2 EP0999349 A2 EP 0999349A2 EP 99810971 A EP99810971 A EP 99810971A EP 99810971 A EP99810971 A EP 99810971A EP 0999349 A2 EP0999349 A2 EP 0999349A2
Authority
EP
European Patent Office
Prior art keywords
cover
blades
outer ring
axial
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.)
Granted
Application number
EP99810971A
Other languages
German (de)
English (en)
Other versions
EP0999349A3 (fr
EP0999349B1 (fr
Inventor
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
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 EP0999349A2 publication Critical patent/EP0999349A2/fr
Publication of EP0999349A3 publication Critical patent/EP0999349A3/fr
Application granted granted Critical
Publication of EP0999349B1 publication Critical patent/EP0999349B1/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
    • 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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator

Definitions

  • the invention relates to an axial turbine according to the preamble of claim 1.
  • the essential components of the axial turbines of turbomachines are Rotor with the blades, the nozzle ring and the cover for the blades. Inevitable manufacturing and assembly tolerances result in the flow channel such axial turbines small discontinuities, which is a reduction efficiency.
  • An axial turbine of an exhaust gas turbocharger is known from EP 806 547 A1, which when operating the internal combustion engine connected to it, relatively high temperatures is exposed.
  • the turbine-side components such as e.g. the gas inlet housing, the nozzle ring, the cover and the gas outlet housing high thermal stresses.
  • the component temperatures differ accordingly.
  • the consequence are different thermal expansions with relative movements between the individual components, which lead to screw breaks, gas leaks and component tears being able to lead. That is why the formation and arrangement of the separation points plays a role of gas inlet housing, gas outlet housing, nozzle ring and cover play an essential role in the functionality of the axial turbine and thus the Exhaust gas turbocharger.
  • EP 806 548 A1 is one Known solution for simple and secure attachment of the nozzle ring.
  • To the nozzle ring lies with its outer ring on the cover and with its inner ring on the gas inlet housing.
  • an axial and between the outer ring and the gas outlet housing a radial expansion gap is formed.
  • the invention tries to avoid all these disadvantages. It is based on the task to create an axial turbine with improved efficiency. In addition the assembly and disassembly options are to be expanded.
  • this is achieved in that with a device according to the preamble of claim 1, the parting line from the outer ring of the nozzle ring to cover the rotor blade side by half the gap width of the axial gap trending, imaginary level is arranged.
  • the parting line between the outer ring and the cover is particularly advantageous arranged upstream of the blades.
  • almost the whole Gap width of the axial gap is formed without discontinuities, which means another Enhancing the efficiency of the axial turbine is made possible.
  • the inner contour of the cover is also radial is arranged outside the inner contour of the outer ring. In this case creates a step with a so-called positive blade overlap, which overflow of the blades in their upstream region is reduced and in combination with the significantly reduced discontinuity to a disproportionate Can increase efficiency.
  • a console in the direction of Covering ridge arranged. This bridge reduces the gap losses in the radial gap formed between the blades and the cover.
  • the axial turbine of an exhaust gas turbocharger shown in FIG. 1 as prior art has one formed by a gas inlet and a gas outlet housing 1, 2 Turbine housing 3, which by means of connecting elements designed as screws 4 is held together.
  • the turbine housing 3 is one of one Shaft 5 supported rotor 6 with blades 7 arranged.
  • the rotor 6 will bounded on the outside by a cover 8 designed as a diffuser, which in turn via a flange 9 and by means of screws 10 on the gas outlet housing 2 is attached.
  • another internal combustion engine can be connected to the exhaust gas turbocharger.
  • nozzle ring 15 Upstream of the blades 7 is in the flow channel 11 from an outer ring 12, an inner ring 13 and a number of guide vanes formed therebetween 14 existing and formed as a casting nozzle ring 15.
  • the latter is clamped axially between the cover 8 and the gas inlet housing 1 and arranged radially within the gas outlet housing 2.
  • the inner ring 13 is by means of several Positioning elements 16 designed as pins are secured against rotation on the gas inlet housing 1 supported.
  • a parting line 17 Between the outer ring 12 of the nozzle ring 15 and the Cover 8 is a parting line 17 (Fig. 1).
  • the nozzle ring 15 also from other materials, such as sheet metal or steel profiles are made or made of ceramic.
  • FIG. 2 shows an enlarged section of FIG. 1, which is a first one Embodiment of the invention shows.
  • Between the blades 7 and the Guide vanes 14 of the axial turbine have an axial gap 18 with a gap width 19.
  • the parting line 17 of the outer ring 12 of the nozzle ring 15 and the cover 8 is on the rotor blade side through half the gap width 19 of the axial gap 18 extending, imaginary level 20 arranged.
  • A is shown advantageous arrangement, arranged with an upstream of the blades 7 Parting line 17.
  • both the cover 8 of the moving blades have 7 and the outer ring 12 of the nozzle ring 15 have an inner contour 21, 22, with the inner contour 21 of the cover 8 radially outside the inner contour 22 of the outer ring 12 is arranged (Fig. 3).
  • a blade profile 23 of the moving blade 7 is shown in FIG has a pressure side 24, a suction side 25 and a blade tip 26.
  • a blade profile 23 both on the pressure side and on the suction side outstanding console 27 and a console 27 in the direction of the cover 8 projecting web 28 arranged (Fig. 4).
  • the web 28 also reduces any Gap losses in the formed between the blades 7 and the cover 8 Radial gap 29.
EP99810971A 1998-11-04 1999-10-27 Turbine axiale Expired - Lifetime EP0999349B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19850732A DE19850732A1 (de) 1998-11-04 1998-11-04 Axialturbine
DE19850732 1998-11-04

Publications (3)

Publication Number Publication Date
EP0999349A2 true EP0999349A2 (fr) 2000-05-10
EP0999349A3 EP0999349A3 (fr) 2002-03-13
EP0999349B1 EP0999349B1 (fr) 2005-05-11

Family

ID=7886598

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99810971A Expired - Lifetime EP0999349B1 (fr) 1998-11-04 1999-10-27 Turbine axiale

Country Status (7)

Country Link
US (1) US6318961B1 (fr)
EP (1) EP0999349B1 (fr)
JP (1) JP2000145407A (fr)
KR (1) KR100656721B1 (fr)
CN (2) CN2403896Y (fr)
DE (2) DE19850732A1 (fr)
TW (1) TW460656B (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1710395A2 (fr) 2005-03-31 2006-10-11 Hitachi, Ltd. Turbine axiale
EP2781695A1 (fr) * 2013-03-22 2014-09-24 ABB Turbo Systems AG Aubes de guidage d'une turbine à gaz d'échappement

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19913269A1 (de) * 1999-03-24 2000-09-28 Asea Brown Boveri Turbinenschaufel
US7270519B2 (en) * 2002-11-12 2007-09-18 General Electric Company Methods and apparatus for reducing flow across compressor airfoil tips
US6779979B1 (en) * 2003-04-23 2004-08-24 General Electric Company Methods and apparatus for structurally supporting airfoil tips
US7596949B2 (en) * 2006-02-23 2009-10-06 General Electric Company Method and apparatus for heat shielding gas turbine engines
WO2010085494A1 (fr) * 2009-01-20 2010-07-29 Williams International Co., L.L.C. Turbocompresseur avec cartouche de tuyère de turbine
DE102009045167A1 (de) * 2009-09-30 2011-04-07 Man Diesel & Turbo Se Turbine eines Abgasturbolader
US8926270B2 (en) * 2010-12-17 2015-01-06 General Electric Company Low-ductility turbine shroud flowpath and mounting arrangement therefor
DE102011080596A1 (de) * 2011-08-08 2013-02-14 Abb Turbo Systems Ag Anordnung für ein Leiten eines Abgases in einer axial angeströmten Abgasturbine
JP5934806B2 (ja) * 2011-12-20 2016-06-15 ゲーコーエヌ エアロスペース スウェーデン アーベー ガスタービンエンジン構成部品の製造方法
US10087764B2 (en) 2012-03-08 2018-10-02 Pratt & Whitney Canada Corp. Airfoil for gas turbine engine
CN108590778B (zh) * 2018-01-15 2020-09-04 重庆江增船舶重工有限公司 一种轴流式有机工质透平膨胀机
DE102018212334B4 (de) * 2018-07-24 2024-04-11 Vitesco Technologies GmbH Abgasturbolader mit Turbinenrad mit Winglets
CN115585055A (zh) * 2022-11-04 2023-01-10 重庆金皇后新能源汽车制造有限公司 一种加力大环转换器、传动系统及汽车

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0806548A1 (fr) 1996-05-08 1997-11-12 Asea Brown Boveri AG Turbine d'un turbocompresseur à gaz d'échappement
EP0806547A1 (fr) 1996-05-08 1997-11-12 Asea Brown Boveri AG Turbine axiale pour turbocompresseurs

Family Cites Families (15)

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Publication number Priority date Publication date Assignee Title
US2849209A (en) * 1950-10-11 1958-08-26 Gen Electric Nozzle construction for turbines
US3067983A (en) * 1958-07-01 1962-12-11 Gen Motors Corp Turbine mounting construction
US2980396A (en) * 1959-06-29 1961-04-18 Gen Electric Stator construction for turbine engines
CH482915A (de) * 1967-11-03 1969-12-15 Sulzer Ag Leitvorrichtung für Axialturbine
US3817655A (en) * 1972-11-22 1974-06-18 Carrier Corp Stator blade mounting structure for turbomachines
US3867060A (en) * 1973-09-27 1975-02-18 Gen Electric Shroud assembly
DE2405050A1 (de) * 1974-02-02 1975-08-07 Motoren Turbinen Union Laufschaufeln fuer turbomaschinen
GB1493913A (en) * 1975-06-04 1977-11-30 Gen Motors Corp Turbomachine stator interstage seal
US3985465A (en) * 1975-06-25 1976-10-12 United Technologies Corporation Turbomachine with removable stator vane
JPS5436161Y2 (fr) * 1975-08-01 1979-11-01
GB2061396B (en) * 1979-10-24 1983-05-18 Rolls Royce Turbine blade tip clearance control
US4684320A (en) * 1984-12-13 1987-08-04 United Technologies Corporation Axial flow compressor case
SU1480776A3 (ru) * 1985-02-20 1989-05-15 Ббц Аг Браун, Бовери Унд Ко. (Фирма) Турбонагнетатель двигател внутреннего сгорани
US5618161A (en) * 1995-10-17 1997-04-08 Westinghouse Electric Corporation Apparatus for restraining motion of a turbo-machine stationary vane
US5738490A (en) * 1996-05-20 1998-04-14 Pratt & Whitney Canada, Inc. Gas turbine engine shroud seals

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0806548A1 (fr) 1996-05-08 1997-11-12 Asea Brown Boveri AG Turbine d'un turbocompresseur à gaz d'échappement
EP0806547A1 (fr) 1996-05-08 1997-11-12 Asea Brown Boveri AG Turbine axiale pour turbocompresseurs

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7901179B2 (en) 2004-06-03 2011-03-08 Hitachi, Ltd. Axial turbine
EP1710395A2 (fr) 2005-03-31 2006-10-11 Hitachi, Ltd. Turbine axiale
EP1710395A3 (fr) * 2005-03-31 2010-07-21 Hitachi, Ltd. Turbine axiale
US8308421B2 (en) 2005-03-31 2012-11-13 Hitachi, Ltd. Axial turbine
EP2781695A1 (fr) * 2013-03-22 2014-09-24 ABB Turbo Systems AG Aubes de guidage d'une turbine à gaz d'échappement

Also Published As

Publication number Publication date
US6318961B1 (en) 2001-11-20
DE59912034D1 (de) 2005-06-16
CN2403896Y (zh) 2000-11-01
EP0999349A3 (fr) 2002-03-13
EP0999349B1 (fr) 2005-05-11
DE19850732A1 (de) 2000-05-11
JP2000145407A (ja) 2000-05-26
TW460656B (en) 2001-10-21
KR100656721B1 (ko) 2006-12-15
KR20000035199A (ko) 2000-06-26
CN1144935C (zh) 2004-04-07
CN1253230A (zh) 2000-05-17

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