EP0024275A1 - Fixation des anneaux de tuyères - Google Patents

Fixation des anneaux de tuyères Download PDF

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Publication number
EP0024275A1
EP0024275A1 EP79200456A EP79200456A EP0024275A1 EP 0024275 A1 EP0024275 A1 EP 0024275A1 EP 79200456 A EP79200456 A EP 79200456A EP 79200456 A EP79200456 A EP 79200456A EP 0024275 A1 EP0024275 A1 EP 0024275A1
Authority
EP
European Patent Office
Prior art keywords
nozzle ring
locking
turbine blade
blade wheel
rotation
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Withdrawn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
EP79200456A
Other languages
German (de)
English (en)
Inventor
Ambrogio Perego
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
Priority to EP79200456A priority Critical patent/EP0024275A1/fr
Priority to DE19797932231 priority patent/DE7932231U1/de
Publication of EP0024275A1 publication Critical patent/EP0024275A1/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Withdrawn legal-status Critical Current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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the invention relates to the locking of nozzle rings which initiate the inflow of the working medium to the turbine blades in the inflow channel of turbines.
  • the nozzle ring is subjected to high stresses and is directly affected by changing operating conditions, ie increasing or decreasing the pressure and temperature of the incoming working medium.
  • the temperature gradients of the incoming working medium can be large, depending on the operating mode and purpose of the turbine. In such cases, the operating temperature of the incoming working medium in the nozzle ring will set faster than in the surrounding inflow box, due to the much larger volume of material, which may be the case.
  • the different temperature expansions of the different materials also play a role. From this it can be seen that the locking of the nozzle ring in the inflow box is exposed to different temperature expansions and must therefore be designed in such a way that the nozzle ring is constantly locked in place even during surge operation, i.e. when partial pressure prevails, or when the pressure and temperature swell and swell Condition must remain so that the nozzle ring does not deflect, because this would inevitably lead to accidents.
  • Another variant is to compensate for the initially greater thermal expansion of the nozzle ring compared to the inflow box by specifying a seat play.
  • the use of this type of locking means that the seat play is designed for the maximum radial and axial expansion caused by the most extreme operating temperature.
  • intermediate operating conditions e.g. when idling or alternating operation, the nozzle ring inevitably comes out because of the not yet fully used game or because of game formation, with the dreaded consequences.
  • the invention has for its object to provide a locking of the nozzle ring, which can compensate the temperature expansion differences between the nozzle ring and inflow box without damage and effectively.
  • the advantage of the invention can be seen in particular in the fact that the prestressed spring element acts non-positively on the nozzle ring at any operating temperature, as a result of which the friction force that is generated presses it firmly into its inflow box seat and, as a result, cannot deflect it.
  • the spring element is designed as a full circular ring plate, because a good seal against the undesired flow around the nozzle ring is also achieved at the same time.
  • the figures show the turbine of an exhaust gas turbocharger of radial design.
  • the nozzle ring 2 consists of a circular top plate 1 and a likewise circular bottom plate 3;
  • guide vanes which are not shown, are arranged in the circumferential direction, which show the inflow of the working medium from the inflow channel 18 in the direction of the arrow to the turbine view finely initiate 9, the latter in turn in environmental f longitudinal direction are arranged on the turbine impeller lla.
  • the recess 7 in the inflow box on the turbine blade wheel side 17b forms the seat of the nozzle ring 2, the nozzle ring lower plate 3 resting on the seat surface 14.
  • This recess 7 has a nozzle ring play 13 in the radial direction, so that the different temperature expansions between the nozzle ring lower plate 3 and the inflow box on the turbine blade wheel side 17b, be it material-related or due to the temporally different expansion course, can be absorbed.
  • the cage 28 in favor of the nozzle ring top plate 1 is also in the radial direction with respect to connector 10 and Einströmkasten t urbinenwellen matter 17a, a nozzle ring 13 is provided game.
  • the wedge 5 used for the positive locking is attached to the seat surface 14 of the nozzle ring lower plate 3.
  • the keyway 4 is excluded in the inflow box on the turbine blade wheel side 17b, a keyway play 6 absorbs the different temperature expansions which are also caused by the material or result from the temporally different expansion course.
  • the circular ring plate 8 forming the spring element is supported in a ring shape on the attachment 12 in the cage 28 and also presses in a ring shape on the contact surface 15 of the nozzle ring top plate shoulder 16. Attachment 12 and contact surface 15 are dimensionally matched so that the circular ring plate 8 is biased in the cold state.
  • FIG. 2 only has a different arrangement of the wedge used to ensure the positive locking.
  • the wedge 19 is on the turbine blade wheel side in the inflow box. 17b recessed and protrudes from the seat 14. Keyway 20 and keyway play 21 are excluded on the underside of the nozzle ring lower plate 3.
  • the positive locking in the circumferential direction to the turbine blade wheel 11a is ensured by a polygonal design of the circumference 23 of the nozzle ring lower plate 3 and, correspondingly, the adjacent wall 22 of the nozzle ring seat 7.
  • a game 24 catches the temperature expansions.
  • the axial frictional connection ensures the annular plate, as has been described above under FIG. 1.
  • the variant is shown in which the annular plate 8 takes over both the axial frictional connection and the form-fitting locking in the direction of rotation to the turbine blade wheel 11a.
  • the shoulder 16 of the nozzle ring top plate 1 has a rectangular cutout 27.
  • a nose 25 is formed on the circumference of the circular ring plate 8.
  • the circular ring plate 8 now exerts the axial frictional engagement on the contact surface 26 of the milling 27, while the wedge-like structure between the nose 25 and the milling 27 ensures the positive locking in the direction of rotation to the turbine blade wheel 11a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP79200456A 1979-08-15 1979-08-15 Fixation des anneaux de tuyères Withdrawn EP0024275A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP79200456A EP0024275A1 (fr) 1979-08-15 1979-08-15 Fixation des anneaux de tuyères
DE19797932231 DE7932231U1 (de) 1979-08-15 1979-11-15 Arretierung von duesenringen

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP79200456A EP0024275A1 (fr) 1979-08-15 1979-08-15 Fixation des anneaux de tuyères

Publications (1)

Publication Number Publication Date
EP0024275A1 true EP0024275A1 (fr) 1981-03-04

Family

ID=8186300

Family Applications (1)

Application Number Title Priority Date Filing Date
EP79200456A Withdrawn EP0024275A1 (fr) 1979-08-15 1979-08-15 Fixation des anneaux de tuyères

Country Status (2)

Country Link
EP (1) EP0024275A1 (fr)
DE (1) DE7932231U1 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0160460A2 (fr) * 1984-04-20 1985-11-06 Allied-Signal Inc. Turbosoufflante à gaz d'échappement
EP0238038A2 (fr) * 1986-03-17 1987-09-23 Hitachi, Ltd. Turbine à gaz d'échappement
EP0856639A2 (fr) 1997-01-29 1998-08-05 Asea Brown Boveri AG Anneau de guidage pour une turbine radiale
EP0985803A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Etage de turbine avec entrée radiale et sortie axiale
WO2008139130A1 (fr) * 2007-05-10 2008-11-20 Cummins Turbo Technologies Limited Turbine à géométrie variable
DE102016125189A1 (de) * 2016-12-21 2018-06-21 Man Diesel & Turbo Se Turbolader
CN110023589A (zh) * 2016-12-01 2019-07-16 曼恩能源方案有限公司 涡轮增压器
DE102021108686A1 (de) 2021-04-07 2022-10-13 Borgwarner Inc. Turbinenanordnung mit separater leiteinrichtung
DE102022105348A1 (de) 2022-03-08 2023-09-14 Avl Schrick Gmbh Abgasturboladerfixierung
WO2023228467A1 (fr) * 2022-05-25 2023-11-30 株式会社Ihi Turbine et compresseur de suralimentation
DE102022118731A1 (de) 2022-07-26 2024-02-01 Rolls-Royce Solutions GmbH Turbinenanordnungen, Turbolader und Brennkraftmaschine

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR709066A (fr) * 1930-01-24 1931-08-03 Asea Ab Dispositif perfectionné de montage d'une enveloppe intérieure dans une enveloppe extérieure
US2668006A (en) * 1949-11-08 1954-02-02 Baldwin Lima Hamilton Corp Turbocharger
US2918207A (en) * 1957-12-16 1959-12-22 Gen Motors Corp Turbocharger
US3010697A (en) * 1958-06-16 1961-11-28 Thompson Ramo Wooldridge Inc Turbocharger
FR1279042A (fr) * 1961-02-03 1961-12-15 Licentia Gmbh Turbine axiale comprenant un ensemble de supports d'aubes directrices
US3199294A (en) * 1961-04-25 1965-08-10 Bmw Triebwerkbau Gmbh Air-cooled support and guide vane assembly for a gas turbine engine
CH470641A (de) * 1967-10-04 1969-03-31 Linde Ag Düsenring für Turbinen, insbesondere für Entspannungsturbinen in der Tief- bzw. Tiefsttemperaturtechnik
DE1576960A1 (de) * 1967-09-07 1970-06-04 Linde Ag Entspannungsturbine fuer tiefe bzw.sehr tiefe Temperaturen in Zentripedalbauart
FR2197420A5 (fr) * 1972-08-25 1974-03-22 Cav Ltd
FR2246782A1 (en) * 1973-10-01 1975-05-02 Gen Electric Sealing ring with initial preloading - has axially projecting lip at inner or outer edge of radial surfaces
GB1473248A (en) * 1975-01-04 1977-05-11 G Sojuz Ni Traktor I Turbochargers

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR709066A (fr) * 1930-01-24 1931-08-03 Asea Ab Dispositif perfectionné de montage d'une enveloppe intérieure dans une enveloppe extérieure
US2668006A (en) * 1949-11-08 1954-02-02 Baldwin Lima Hamilton Corp Turbocharger
US2918207A (en) * 1957-12-16 1959-12-22 Gen Motors Corp Turbocharger
US3010697A (en) * 1958-06-16 1961-11-28 Thompson Ramo Wooldridge Inc Turbocharger
FR1279042A (fr) * 1961-02-03 1961-12-15 Licentia Gmbh Turbine axiale comprenant un ensemble de supports d'aubes directrices
US3199294A (en) * 1961-04-25 1965-08-10 Bmw Triebwerkbau Gmbh Air-cooled support and guide vane assembly for a gas turbine engine
DE1576960A1 (de) * 1967-09-07 1970-06-04 Linde Ag Entspannungsturbine fuer tiefe bzw.sehr tiefe Temperaturen in Zentripedalbauart
CH470641A (de) * 1967-10-04 1969-03-31 Linde Ag Düsenring für Turbinen, insbesondere für Entspannungsturbinen in der Tief- bzw. Tiefsttemperaturtechnik
FR2197420A5 (fr) * 1972-08-25 1974-03-22 Cav Ltd
FR2246782A1 (en) * 1973-10-01 1975-05-02 Gen Electric Sealing ring with initial preloading - has axially projecting lip at inner or outer edge of radial surfaces
GB1473248A (en) * 1975-01-04 1977-05-11 G Sojuz Ni Traktor I Turbochargers

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0160460A2 (fr) * 1984-04-20 1985-11-06 Allied-Signal Inc. Turbosoufflante à gaz d'échappement
EP0160460A3 (en) * 1984-04-20 1987-11-04 The Garrett Corporation Turbocharger
EP0238038A2 (fr) * 1986-03-17 1987-09-23 Hitachi, Ltd. Turbine à gaz d'échappement
EP0238038A3 (en) * 1986-03-17 1989-06-07 Hitachi, Ltd. Gas turbine driven by exhaust gas from internal combustion engine and method of controlling the same
EP0856639A2 (fr) 1997-01-29 1998-08-05 Asea Brown Boveri AG Anneau de guidage pour une turbine radiale
US5964574A (en) * 1997-01-29 1999-10-12 Asea Brown Boveri Ag Exhaust-gas turbine of a turbocharger
EP0856639A3 (fr) * 1997-01-29 2000-04-19 Asea Brown Boveri AG Anneau de guidage pour une turbine radiale
EP0985803A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Etage de turbine avec entrée radiale et sortie axiale
WO2008139130A1 (fr) * 2007-05-10 2008-11-20 Cummins Turbo Technologies Limited Turbine à géométrie variable
GB2461216A (en) * 2007-05-10 2009-12-30 Cummins Turbo Tech Ltd Variable geometry turbine
GB2461216B (en) * 2007-05-10 2011-11-30 Cummins Turbo Tech Ltd Variable geometry turbine
CN110023589A (zh) * 2016-12-01 2019-07-16 曼恩能源方案有限公司 涡轮增压器
DE102016125189A1 (de) * 2016-12-21 2018-06-21 Man Diesel & Turbo Se Turbolader
DE102016125189B4 (de) * 2016-12-21 2020-11-26 Man Energy Solutions Se Turbolader
DE102021108686A1 (de) 2021-04-07 2022-10-13 Borgwarner Inc. Turbinenanordnung mit separater leiteinrichtung
DE102022105348A1 (de) 2022-03-08 2023-09-14 Avl Schrick Gmbh Abgasturboladerfixierung
WO2023228467A1 (fr) * 2022-05-25 2023-11-30 株式会社Ihi Turbine et compresseur de suralimentation
DE102022118731A1 (de) 2022-07-26 2024-02-01 Rolls-Royce Solutions GmbH Turbinenanordnungen, Turbolader und Brennkraftmaschine

Also Published As

Publication number Publication date
DE7932231U1 (de) 1981-02-19

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Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): CH DE FR GB

17P Request for examination filed

Effective date: 19810421

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: BBC AKTIENGESELLSCHAFT BROWN, BOVERI & CIE.

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 19820726

RIN1 Information on inventor provided before grant (corrected)

Inventor name: PEREGO, AMBROGIO