EP0999349A2 - Axialturbine - Google Patents
Axialturbine Download PDFInfo
- 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
Links
- 238000011144 upstream manufacturing Methods 0.000 claims description 9
- 238000000926 separation method Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 29
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
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.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
Abstract
Description
- Fig. 1
- einen Teillängsschnitt einer Axialturbine des Standes der Technik;
- Fig. 2
- einen vergrösserten Ausschnitt aus Fig. 1, mit der erfindungsgemässen Ausbildung des Düsenringes;
- Fig. 3
- eine Darstellung gemäss Fig. 2, jedoch in einem zweiten Ausführungsbeispiel;
- Fig. 4
- einen Schnitt durch eine Laufschaufel entlang der Linie IV-IV in Fig. 3.
- 1
- Gaseintrittgehäuse
- 2
- Gasaustrittgehäuse
- 3
- Turbinengehäuse
- 4
- Verbindungselement, Schraube
- 5
- Welle
- 6
- Rotor
- 7
- Laufschaufel
- 8
- Abdeckung, Diffusor
- 9
- Flansch
- 10
- Schraube
- 11
- Strömungskanal
- 12
- Aussenring
- 13
- Innenring
- 14
- Leitschaufel
- 15
- Düsenring
- 16
- Positionierlement, Stift
- 17
- Trennfuge
- 18
- Axialspalt
- 19
- Spaltweite
- 20
- Ebene, in halber Spaltweite
- 21
- Innenkontur, von 8
- 22
- Innenkontur, von 12
- 23
- Schaufelprofil
- 24
- Druckseite
- 25
- Saugseite
- 26
- Schaufelspitze
- 27
- Konsole
- 28
- Steg
- 29
- Radialspalt
Claims (5)
- Axialturbine mit einem eine Anzahl Laufschaufeln (7) tragenden Rotor (6), mit einem stromauf der Laufschaufeln (7) angeordneten, aus einem Aussenring (12), einem Innenring (13) und aus einer Anzahl dazwischen angeordneter Leitschaufeln (14) bestehenden Düsenring (15), mit einem zwischen den Laufschaufeln (7) und den Leitschaufeln (14) ausgebildeten, eine Spaltweite (19) aufweisenden Axialspalt (18) und mit einer die Laufschaufeln (7) nach aussen begrenzenden Abdeckung (8), wobei zwischen dem Aussenring (12) des Düsenrings (15) und der Abdeckung (8) eine Trennfuge (17) ausgebildet ist, dadurch gekennzeichnet, dass die Trennfuge (17) von Aussenring (12) und Abdeckung (8) laufschaufelseitig einer durch die halbe Spaltweite (19) des Axialspaltes (18) verlaufenden, gedachten Ebene (20) angeordnet ist.
- Axialturbine nach Anspruch 1, dadurch gekennzeichnet, dass die Trennfuge (17) von Aussenring (12) und Abdeckung (8) unmittelbar stromauf der Laufschaufeln (7) angeordnet ist.
- Axialturbine nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass sowohl die Abdeckung (8) als auch der Aussenring (12) eine Innenkontur (21, 22) aufweisen, wobei die Innenkontur (21) der Abdeckung (8) radial ausserhalb der Innenkontur (22) des Aussenringes (12) angeordnet ist.
- Axialturbine nach Anspruch 3, dadurch gekennzeichnet, dass jede Laufschaufel (7) ein Schaufelprofil (23) mit einer Druckseite (24), einer Saugseite (25) und mit einer Schaufelspitze (26) aufweist, wobei an der Schaufelspitze (26) eine das Schaufelprofil (23) zumindest druckseitig überragende Konsole (27) angeordnet ist.
- Axialturbine nach Anspruch 4, dadurch gekennzeichnet, dass an der Schaufelspitze (26) ein die Konsole (27) in Richtung der Abdeckung (8) überragender Steg (28) angeordnet ist.
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 (de) | 2000-05-10 |
EP0999349A3 EP0999349A3 (de) | 2002-03-13 |
EP0999349B1 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 (de) |
EP (1) | EP0999349B1 (de) |
JP (1) | JP2000145407A (de) |
KR (1) | KR100656721B1 (de) |
CN (2) | CN1144935C (de) |
DE (2) | DE19850732A1 (de) |
TW (1) | TW460656B (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1710395A2 (de) | 2005-03-31 | 2006-10-11 | Hitachi, Ltd. | Axial Turbine |
EP2781695A1 (de) * | 2013-03-22 | 2014-09-24 | ABB Turbo Systems AG | Leitvorrichtung einer Abgasturbine |
Families Citing this family (13)
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 |
EP3168429B1 (de) * | 2009-01-20 | 2018-03-07 | Williams International Co., L.L.C. | Turbinenleitradkartusche zur verwendung mit einem turboladerkern |
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 |
US9803551B2 (en) * | 2011-12-20 | 2017-10-31 | Gkn Aerospace Sweden Ab | Method for manufacturing of a gas turbine engine component |
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***及汽车 |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0806547A1 (de) | 1996-05-08 | 1997-11-12 | Asea Brown Boveri AG | Axialturbine eines Abgasturboladers |
EP0806548A1 (de) | 1996-05-08 | 1997-11-12 | Asea Brown Boveri AG | Abgasturbine eines Abgasturboladers |
Family Cites Families (15)
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 (de) * | 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 |
-
1998
- 1998-11-04 DE DE19850732A patent/DE19850732A1/de not_active Withdrawn
-
1999
- 1999-10-27 EP EP99810971A patent/EP0999349B1/de not_active Expired - Lifetime
- 1999-10-27 TW TW088118573A patent/TW460656B/zh not_active IP Right Cessation
- 1999-10-27 DE DE59912034T patent/DE59912034D1/de not_active Expired - Lifetime
- 1999-11-01 US US09/431,177 patent/US6318961B1/en not_active Expired - Lifetime
- 1999-11-02 JP JP11312545A patent/JP2000145407A/ja active Pending
- 1999-11-03 KR KR1019990048332A patent/KR100656721B1/ko active IP Right Grant
- 1999-11-04 CN CNB991235177A patent/CN1144935C/zh not_active Expired - Lifetime
- 1999-11-04 CN CN99252706U patent/CN2403896Y/zh not_active Expired - Lifetime
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0806547A1 (de) | 1996-05-08 | 1997-11-12 | Asea Brown Boveri AG | Axialturbine eines Abgasturboladers |
EP0806548A1 (de) | 1996-05-08 | 1997-11-12 | Asea Brown Boveri AG | Abgasturbine eines Abgasturboladers |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7901179B2 (en) | 2004-06-03 | 2011-03-08 | Hitachi, Ltd. | Axial turbine |
EP1710395A2 (de) | 2005-03-31 | 2006-10-11 | Hitachi, Ltd. | Axial Turbine |
EP1710395A3 (de) * | 2005-03-31 | 2010-07-21 | Hitachi, Ltd. | Axial Turbine |
US8308421B2 (en) | 2005-03-31 | 2012-11-13 | Hitachi, Ltd. | Axial turbine |
EP2781695A1 (de) * | 2013-03-22 | 2014-09-24 | ABB Turbo Systems AG | Leitvorrichtung einer Abgasturbine |
Also Published As
Publication number | Publication date |
---|---|
KR100656721B1 (ko) | 2006-12-15 |
CN2403896Y (zh) | 2000-11-01 |
JP2000145407A (ja) | 2000-05-26 |
KR20000035199A (ko) | 2000-06-26 |
EP0999349B1 (de) | 2005-05-11 |
DE19850732A1 (de) | 2000-05-11 |
CN1253230A (zh) | 2000-05-17 |
DE59912034D1 (de) | 2005-06-16 |
TW460656B (en) | 2001-10-21 |
CN1144935C (zh) | 2004-04-07 |
EP0999349A3 (de) | 2002-03-13 |
US6318961B1 (en) | 2001-11-20 |
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