EP0999349B1 - Axialturbine - Google Patents

Axialturbine Download PDF

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Publication number
EP0999349B1
EP0999349B1 EP99810971A EP99810971A EP0999349B1 EP 0999349 B1 EP0999349 B1 EP 0999349B1 EP 99810971 A EP99810971 A EP 99810971A EP 99810971 A EP99810971 A EP 99810971A EP 0999349 B1 EP0999349 B1 EP 0999349B1
Authority
EP
European Patent Office
Prior art keywords
cover
blades
outer ring
blade
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.)
Expired - Lifetime
Application number
EP99810971A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0999349A3 (de
EP0999349A2 (de
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
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 filed Critical ABB Turbo Systems AG
Publication of EP0999349A2 publication Critical patent/EP0999349A2/de
Publication of EP0999349A3 publication Critical patent/EP0999349A3/de
Application granted granted Critical
Publication of EP0999349B1 publication Critical patent/EP0999349B1/de
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
    • 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
    • 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.
  • Essential components of the axial turbines of turbomachines are the Rotor with the blades, the nozzle ring and the cover for the blades. Due to unavoidable manufacturing and assembly tolerances arise in the flow channel such axial turbines small discontinuities, which is a reduction the efficiency result.
  • the mostly cast nozzle ring which is arranged between the stationary housing parts and the rotating blades of an axial turbine.
  • EP 806 548 A1 a solution for simple and secure attachment of the nozzle ring is known.
  • 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 blades are arranged in a stepped manner to the guide vanes combined in the nozzle ring and have a positive overlap, ie in the region of the rotor blades, the inner contour of the cover is arranged radially further outside than in the area of the guide vanes, similar to what is disclosed in US Pat. Nos. 2,849,209 and 4,006,345.
  • a configuration has the disadvantage during disassembly that the axial turbine can only be moved in the opposite direction to the nozzle ring and not in both directions.
  • the invention seeks to avoid all these disadvantages. It is the object of the invention to provide an axial turbine with improved efficiency. In addition, the assembly and disassembly options are to be expanded. According to the invention, this is achieved in that, in a device according to the preamble of claim 1, the parting line from the outer ring of the nozzle ring to the cover blade side of an extending through half the gap width of the axial gap, imaginary plane, located immediately upstream of the blades.
  • the outer ring of the nozzle ring is extended in the direction of the blades, so that the flow channel over almost the entire gap width of the axial gap has no discontinuity.
  • an improvement of the flow conditions and the efficiency of the axial turbine can be achieved.
  • the inner contour of the cover is arranged radially outside the inner contour of the outer ring. In this case, a step is created with a so-called positive blade overlap, which reduces overflow of the blades in the upstream region and in combination with the significantly reduced discontinuity can lead to a disproportionate increase in efficiency.
  • each blade which is equipped with a pressure side, a suction side and with a blade tip
  • a bracket projecting beyond the blade profile at least on the pressure side is arranged on the blade tip.
  • a similar construction has the sheet in GB 1491556, and further, however, for fixing, the sheet in US 3532437. Due to the forming in the region of the console vortex, the efficiency-detrimental overflow of the blade tip can be significantly reduced.
  • FIG. 1 The illustrated in Fig. 1 as the prior art axial turbine of an exhaust gas turbocharger has one of a gas inlet and a gas outlet housing 1, 2 formed Turbine housing 3, which by means of fasteners designed as screws 4 is held together.
  • Turbine housing 3 In the turbine housing 3 is one of a Shaft 5 supported rotor 6 with blades 7 arranged.
  • the rotor 6 is bounded on the outside by a diffuser designed as a cover 8, which in turn via a flange 9 and by means of screws 10 on the gas outlet housing 2 is attached.
  • a flow channel 11 formed, which the exhaust gases of a, not shown, with the diesel engine connected to the exhaust gas turbocharger receives and to the blades 7 of the rotor 6 forwards.
  • another internal combustion engine be connected to the exhaust gas turbocharger.
  • a casting nozzle ring 15 Upstream of the blades 7 is in the flow channel 11 a from an outer ring 12, an inner ring 13 and a number of guide vanes formed therebetween 14 existing and designed as a casting nozzle ring 15 is arranged.
  • the latter is clamped axially between the cover 8 and the gas inlet housing 1 and arranged radially inside the gas outlet housing 2. It lies to that the nozzle ring 15 with its outer ring 12 on the cover 8 and with his Inner ring 13 on the gas inlet housing 1 at.
  • the inner ring 13 is by means of several formed as pins Positionierlementen 16 against rotation on the gas inlet housing 1 supported.
  • a parting line 17 is formed (Fig. 1).
  • the nozzle ring 15 also from other materials, such as sheet metal or steel profiles be made or made of ceramic.
  • FIG. 2 shows an enlarged detail of FIG. 1, which shows a first Embodiment of the invention shows.
  • 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 the bucket side one through half the gap width 19 of the axial gap 18 extending imaginary plane 20 arranged. Shown is a advantageous arrangement, arranged with a directly upstream of the blades 7 Parting line 17.
  • the nozzle ring 15 has the task of the exhaust gases optimally to the To guide blades 7 of the rotor 6.
  • the thus driven rotor 6 provides in turn for driving the associated with him, not shown compressor.
  • the compressed air in the compressor becomes charged, i. to increase performance used the diesel engine.
  • both the cover 8 of the blades 7 and the outer ring 12 of the nozzle ring 15 an inner contour 21, 22, wherein the inner contour 21 of the cover 8 radially outside the inner contour 22 of the outer ring 12 is arranged (Fig. 3).
  • the Axial turbine despite the use of such an advantageous blade cover, be removed on both sides after removing the nozzle ring 15, which so far was not possible.
  • a blade profile 23 of the blade 7 is shown in Fig. 3, which a pressure side 24, a suction side 25 and a blade tip 26 has.
  • a blade profile 23 both pressure and suction side superior console 27 and the console 27 in the direction of the cover. 8 superior ridge 28 arranged (Fig. 4).
  • the bridge reduces 28 possible Gap losses formed in between the blades 7 and the cover 8 Radial gap 29.
EP99810971A 1998-11-04 1999-10-27 Axialturbine Expired - Lifetime EP0999349B1 (de)

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 EP0999349A2 (de) 2000-05-10
EP0999349A3 EP0999349A3 (de) 2002-03-13
EP0999349B1 true EP0999349B1 (de) 2005-05-11

Family

ID=7886598

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99810971A Expired - Lifetime EP0999349B1 (de) 1998-11-04 1999-10-27 Axialturbine

Country Status (7)

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

Families Citing this family (15)

* 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
US7547187B2 (en) 2005-03-31 2009-06-16 Hitachi, Ltd. Axial turbine
US7596949B2 (en) * 2006-02-23 2009-10-06 General Electric Company Method and apparatus for heat shielding gas turbine engines
WO2010085494A1 (en) * 2009-01-20 2010-07-29 Williams International Co., L.L.C. Turbocharger with turbine nozzle cartridge
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
EP2781695A1 (de) * 2013-03-22 2014-09-24 ABB Turbo Systems AG Leitvorrichtung einer Abgasturbine
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 (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4063845A (en) * 1975-06-04 1977-12-20 General Motors Corporation Turbomachine stator interstage seal

Family Cites Families (16)

* Cited by examiner, † Cited by third party
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
US3985465A (en) * 1975-06-25 1976-10-12 United Technologies Corporation Turbomachine with removable stator vane
JPS5436161Y2 (ja) * 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
DE19618314A1 (de) 1996-05-08 1997-11-13 Asea Brown Boveri Abgasturbine eines Abgasturboladers
DE19618313B4 (de) 1996-05-08 2005-07-21 Abb Turbo Systems Ag Axialturbine eines Abgasturboladers
US5738490A (en) * 1996-05-20 1998-04-14 Pratt & Whitney Canada, Inc. Gas turbine engine shroud seals

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4063845A (en) * 1975-06-04 1977-12-20 General Motors Corporation Turbomachine stator interstage seal

Also Published As

Publication number Publication date
US6318961B1 (en) 2001-11-20
DE59912034D1 (de) 2005-06-16
CN2403896Y (zh) 2000-11-01
EP0999349A3 (de) 2002-03-13
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
EP0999349A2 (de) 2000-05-10

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