EP1992789A1 - Carter de turbine à gas d'échappement comprenant un élément de support - Google Patents

Carter de turbine à gas d'échappement comprenant un élément de support Download PDF

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Publication number
EP1992789A1
EP1992789A1 EP07108472A EP07108472A EP1992789A1 EP 1992789 A1 EP1992789 A1 EP 1992789A1 EP 07108472 A EP07108472 A EP 07108472A EP 07108472 A EP07108472 A EP 07108472A EP 1992789 A1 EP1992789 A1 EP 1992789A1
Authority
EP
European Patent Office
Prior art keywords
housing
turbine
flow channel
flange
exhaust gas
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.)
Withdrawn
Application number
EP07108472A
Other languages
German (de)
English (en)
Inventor
Balz Flury
Bent Phillipsen
Daniel Oeschger
Peter Schellenberg
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
Priority to EP07108472A priority Critical patent/EP1992789A1/fr
Priority to PCT/EP2008/056106 priority patent/WO2008142044A2/fr
Publication of EP1992789A1 publication Critical patent/EP1992789A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to the field of exhaust gas turbines, as used in exhaust gas turbochargers, to increase the performance of internal combustion engines (reciprocating engines), or in power turbines, for converting the energy contained in the exhaust gases of internal combustion engines into mechanical or electrical energy. It relates to the housing of such an exhaust gas turbine.
  • asymmetric dimensions of the housing may arise during operational heating due to the thermodynamically optimized, asymmetric shape of the flow channel guide.
  • thermodynamically optimized flow channel shapes In order to prevent damage to the rotating components, the clearance between the rotating components and the stationary housing parts must be increased due to the different sizes, whereby the efficiency gained by the thermodynamically optimized flow channel shapes is at least partially lost again.
  • the object of the invention is to make the gas outlet housing of an exhaust gas turbine resistant to asymmetrical expansion.
  • At least one support element which is arranged in the interior of the gas outlet housing.
  • a partition wall or a rib may be provided, which leads transversely through the flow channel.
  • the gas outlet housing is just as stable as if it had a symmetrical shape.
  • the support element may be provided as an axial connection between the bearing housing-side flange and the gas inlet-side flange. This leads to a further stiffening of the entire turbine housing.
  • the support element is designed as a partition wall, which has a greater radial extent with respect to a narrow rib, or if a plurality of ribs arranged radially one above the other are used, not only axial forces but also a very high moment can be absorbed. The thus achieved, stronger stabilization means that the tilting of the gas outlet flange can be avoided.
  • the asymmetrical housing deformations are so greatly reduced that the efficiency achieved by the thermodynamically optimized flow channel shapes can be fully utilized.
  • the support element causes the natural frequency of the exhaust gas turbine, or the exhaust gas turbocharger or the power turbine increases. This in turn contributes to a much less problematic operating behavior.
  • Fig. 5 shows a cut along the turbine axis turbine housing 10 of an exhaust gas turbocharger or a power turbine according to the prior art.
  • the flow direction of the hot, brought up by the engine exhaust gas is indicated by the thick, white arrows.
  • the gas therefore passes through the opening in the gas inlet flange 13 into the interior of the turbine housing, is guided in the flow channel via the blades of the turbine wheel, not shown, collected radially in the asymmetrically designed collecting chamber 14 outside the diffuser and then leaves the turbine housing via the opening in the gas outlet flange 11.
  • the turbine wheel, not shown, is arranged on a shaft, which is guided through the opening in the bearing housing flange 12 and rotatably mounted in the bearing housing.
  • the compressor in the exhaust gas turbocharger arranged at the power turbine, the connecting element to the utility machine.
  • the diffuser is not shown in the outflow area radially outside the turbine blades.
  • the diffuser is mounted on the back of the gas inlet flange 13 during assembly of the exhaust gas turbine.
  • the holes used for this purpose are shown in the figures.
  • the flow guide on the side of the bearing housing flange 12. This backdrop is either also part of the turbine housing, or else the Bearing housing or it is attached as a separate component during assembly between the bearing housing and the bearing housing flange 12 of the turbine housing.
  • Fig. 1 shows an isometric view of the partially cut turbine housing 10 with an inventive support by a partition wall 15, seen from the side of the bearing housing flange 12 ago.
  • the hot exhaust gas is fed from behind through the opening in the gas inlet flange 13 into the turbine housing.
  • the supporting partition wall 15 extends in the radially outer region of the turbine housing, the gas outlet region in the axial direction of the Lagergepuruseflansch 12 across the flow channel to the side of the gas inlet flange 13.
  • the in the region of the collecting chamber 14, which in the assembled state of the exhaust gas turbine, radially outside extends the turbine housing as described above asymmetrically to effect an increase in efficiency by improved thermodynamic conditions.
  • the supporting partition wall 15 has a stabilizing effect on the turbine housing when unequal expansion occurs due to the asymmetrical shape during heavy heating.
  • Fig. 2 and Fig. 3 show isometric views of the turbine housing 10, wherein the turbine housing is cut through each of the partition wall 15. It can be clearly seen in these illustrations that the partition wall 15 connects the bearing housing side with the gas inlet side, and thus acts as a stabilizer for the turbine housing in the gas outlet region.
  • Figure 4 shows an isometric view of an inventive supported turbine housing in a second embodiment.
  • the gas outlet region is supported by a rib 16.
  • the rib extends transversely through the flow channel and also connects the bearing housing side with the gas inlet side of the turbine housing.
  • two or more ribs may be radially superimposed to provide additional support.
  • a high torque can be absorbed thereby, whereby it can be prevented that the gas outlet flange can tip over.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP07108472A 2007-05-18 2007-05-18 Carter de turbine à gas d'échappement comprenant un élément de support Withdrawn EP1992789A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP07108472A EP1992789A1 (fr) 2007-05-18 2007-05-18 Carter de turbine à gas d'échappement comprenant un élément de support
PCT/EP2008/056106 WO2008142044A2 (fr) 2007-05-18 2008-05-19 Enveloppe de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07108472A EP1992789A1 (fr) 2007-05-18 2007-05-18 Carter de turbine à gas d'échappement comprenant un élément de support

Publications (1)

Publication Number Publication Date
EP1992789A1 true EP1992789A1 (fr) 2008-11-19

Family

ID=38626308

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07108472A Withdrawn EP1992789A1 (fr) 2007-05-18 2007-05-18 Carter de turbine à gas d'échappement comprenant un élément de support

Country Status (2)

Country Link
EP (1) EP1992789A1 (fr)
WO (1) WO2008142044A2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010242752A (ja) * 2009-03-31 2010-10-28 General Electric Co <Ge> タービン・エンジン用の排気プレナム部
WO2019194797A1 (fr) * 2018-04-04 2019-10-10 Siemens Aktiengesellschaft Collecteur de gaz d'échappement pour une turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140047813A1 (en) * 2012-08-17 2014-02-20 Solar Turbines Incorporated Exhaust collector with radial and circumferential flow breaks

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1405090A (en) * 1917-08-24 1922-01-31 British Westinghouse Electric Semidouble-flow steam turbine
US2724545A (en) * 1949-12-05 1955-11-22 Tech Studien Ag Discharge casings for axial flow engines
US2840342A (en) * 1953-03-17 1958-06-24 David H Silvern Turbine exhaust
US3149470A (en) * 1962-08-29 1964-09-22 Gen Electric Low pressure turbine exhaust hood
US3221491A (en) * 1963-04-22 1965-12-07 Laval Turbine Turbine
US4326832A (en) * 1978-11-14 1982-04-27 Tokyo Shibaura Denki Kabushiki Kaisha Exhaust outer casing
DE3108288A1 (de) * 1981-03-05 1982-09-23 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 8900 Augsburg Aufgeladene brennkraftmaschine
EP0345700A1 (fr) * 1988-06-07 1989-12-13 SKODA koncernovy podnik Carter d'échappement pour turbomachine
DE4325457C1 (de) * 1993-07-29 1994-07-28 Man B & W Diesel Ag Abströmgehäuse einer Axialturbine
EP1273760A1 (fr) * 2000-05-10 2003-01-08 General Motors Corporation Turbocompresseur avec accouplement de l'anneau statorique

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2440343B (en) * 2006-07-25 2008-08-13 Siemens Ag A gas turbine arrangement

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1405090A (en) * 1917-08-24 1922-01-31 British Westinghouse Electric Semidouble-flow steam turbine
US2724545A (en) * 1949-12-05 1955-11-22 Tech Studien Ag Discharge casings for axial flow engines
US2840342A (en) * 1953-03-17 1958-06-24 David H Silvern Turbine exhaust
US3149470A (en) * 1962-08-29 1964-09-22 Gen Electric Low pressure turbine exhaust hood
US3221491A (en) * 1963-04-22 1965-12-07 Laval Turbine Turbine
US4326832A (en) * 1978-11-14 1982-04-27 Tokyo Shibaura Denki Kabushiki Kaisha Exhaust outer casing
DE3108288A1 (de) * 1981-03-05 1982-09-23 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 8900 Augsburg Aufgeladene brennkraftmaschine
EP0345700A1 (fr) * 1988-06-07 1989-12-13 SKODA koncernovy podnik Carter d'échappement pour turbomachine
DE4325457C1 (de) * 1993-07-29 1994-07-28 Man B & W Diesel Ag Abströmgehäuse einer Axialturbine
EP1273760A1 (fr) * 2000-05-10 2003-01-08 General Motors Corporation Turbocompresseur avec accouplement de l'anneau statorique

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010242752A (ja) * 2009-03-31 2010-10-28 General Electric Co <Ge> タービン・エンジン用の排気プレナム部
WO2019194797A1 (fr) * 2018-04-04 2019-10-10 Siemens Aktiengesellschaft Collecteur de gaz d'échappement pour une turbine

Also Published As

Publication number Publication date
WO2008142044A2 (fr) 2008-11-27
WO2008142044A3 (fr) 2009-11-19

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