EP0217837B1 - Carter interieur pour turbomachines - Google Patents

Carter interieur pour turbomachines Download PDF

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Publication number
EP0217837B1
EP0217837B1 EP86901793A EP86901793A EP0217837B1 EP 0217837 B1 EP0217837 B1 EP 0217837B1 EP 86901793 A EP86901793 A EP 86901793A EP 86901793 A EP86901793 A EP 86901793A EP 0217837 B1 EP0217837 B1 EP 0217837B1
Authority
EP
European Patent Office
Prior art keywords
shell
inner housing
rings
turbine according
housing
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
Application number
EP86901793A
Other languages
German (de)
English (en)
Other versions
EP0217837A1 (fr
Inventor
Joachim Popp
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0217837A1 publication Critical patent/EP0217837A1/fr
Application granted granted Critical
Publication of EP0217837B1 publication Critical patent/EP0217837B1/fr
Expired 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • housings are generally divided into horizontally (or vertically) divided housings and housings consisting of rings.
  • a pot housing with suspended segments is another known option.
  • the gap control is generally carried out - if any at all - by blowing on the housing over the rotor blades.
  • the ring elements provided with guide vanes are to be arranged between carrier rings, the carrier rings having a separating plane running parallel to the axial direction.
  • This massive and heavy arrangement is surrounded on the outside by insulating material, which makes an easy disassembly of the housing impossible.
  • the invention is also intended to achieve the combination of the advantages of ring and horizontally divided housings.
  • the housing string consists of the annular end housings 1 and 2, the horizontally divided connecting housings 3, 4, 5 and 6, the annular blow-off housings 7 and 8 and the likewise annular lining carriers 9, 10, 11, 12 and 13.
  • the guide vanes are 14, 15 , 16, 17 and 18 marked, the indicated blades with 19, 20, 21, 22, 23 and 24. Furthermore, covers 25, 26, 27 or heat insulation layers 28, 29, 30 and 31 applied.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Une turbomachine comprend un dispositif de réglage de la fente radiale entre le rotor et le carter. Le carter intérieur est composé de parties en forme de coques ayant des sièges de centrage maintenus à une distance déterminée des coques adjacentes. La construction du carter rend celui-ci facile à monter, à démonter et à entretenir. Ce carter peut être utilisé, par exemple, pour turbines à gaz d'avions.

Claims (5)

1. Turbomachine thermique comportant des moyens pour contrôler ou pour maintenir constant l'intervalle radial entre le rotor et le carter interne composé de parties en forme de coquille et qui est exposé, au cours du fonctionnement, à des changements de température, carter dans lequel sont disposés, alternativement et successivement en direction axiale, des anneaux porteurs (9 - 13) et les parties en forme de coquille (1 - 3) de ce carter interne, ces anneaux et ces parties étant reliés entre eux de façon amovible, en ce que des brides de ces parties en forme de coquille (3 - 6) reçoivent entre elles des voiles radiaux périphériques des anneaux porteurs (9 - -13), qui comportent des portées de centrage sur leurs surfaces en regard l'une de l'autre, les parties en forme de coquille (3 - 6) du carter interne comportant un plan de séparation (34), s'étendant parallèlement à la direction axiale et passant par l'axe médian, et les parties des coquilles (de 3 à 6) étant reliées de façon amovible par des vis (35) disposées transversalement à la direction axiale, turbomachine caractérisée en ce que les anneaux porteurs (9-13) constituent des supports de revêtement et que respectivement entre deux supports de revêtement voisins est inséré et maintenu, par interpénétration de formes, le pied d'une aube directrice (15 - 18), tandis que les parties en forme de coquille (3 - 6) du carter interne sont reliées au carter externe (33) par l'intermédiaire d'anneaux de recouvrement (25, 26, 27).
2. Turbomachine selon la revendication 1, caractérisée en ce que les paires de brides des coquilles (3 - 6), qui s'étendent radialement et qui reçoivent entre elles les voiles radiaux des supports de revêtement (9 - -13), sont susceptibles, pour faciliter le montage, d'être écartées l'une de l'autre dans une mesure prédéterminée à chaque ligne de séparation.
3. Turbomachine selon la revendication 1 ou 2, caractérisée en ce que la disposition alternée des parties en forme de coquille (3 - 6) et des parties en forme d'anneau (9-13) de la structure du carter interne est prévue de sorte que ces parties soient maintenues par engrènement de saillies et d'évidements correspondants.
4. Turbomachine selon une des précédentes revendications, caractérisée en ce qu'elle comporte un carter de début et un carter terminal (1, 2) en forme d'anneaux.
5. Turbomachine selon une des précédentes revendications, caractérisée en ce que les parties constitutives (3 - 6 et 9 - 13) de la structure sont à symétrie de révolution et sont alignées coaxialement.
EP86901793A 1985-03-14 1986-03-12 Carter interieur pour turbomachines Expired EP0217837B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3509193 1985-03-14
DE19853509193 DE3509193A1 (de) 1985-03-14 1985-03-14 Stroemungsmaschine mit innengehaeuse

Publications (2)

Publication Number Publication Date
EP0217837A1 EP0217837A1 (fr) 1987-04-15
EP0217837B1 true EP0217837B1 (fr) 1988-11-23

Family

ID=6265228

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86901793A Expired EP0217837B1 (fr) 1985-03-14 1986-03-12 Carter interieur pour turbomachines

Country Status (5)

Country Link
US (1) US4778337A (fr)
EP (1) EP0217837B1 (fr)
JP (1) JPS62502207A (fr)
DE (2) DE3509193A1 (fr)
WO (1) WO1986005546A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4826397A (en) * 1988-06-29 1989-05-02 United Technologies Corporation Stator assembly for a gas turbine engine
US5127794A (en) * 1990-09-12 1992-07-07 United Technologies Corporation Compressor case with controlled thermal environment
CN100406684C (zh) * 2001-11-20 2008-07-30 阿尔斯通技术有限公司 气体涡轮组件
EP2184445A1 (fr) * 2008-11-05 2010-05-12 Siemens Aktiengesellschaft Support d'aubes statorique axialement segmenté d'une turbine à gaz

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL74168C (fr) * 1946-02-25
FR964650A (fr) * 1947-04-16 1950-08-19
CH421142A (de) * 1965-01-12 1966-09-30 Escher Wyss Ag Gehäuse für eine Gas- oder Dampfturbine
CH419184A (de) * 1965-01-12 1966-08-31 Escher Wyss Ag In sich starrer, zwei oder mehr Leitschaufelkränze aufweisender Leitapparat für eine Gas- oder Dampfturbine
US3343806A (en) * 1965-05-27 1967-09-26 Gen Electric Rotor assembly for gas turbine engines
US4023919A (en) * 1974-12-19 1977-05-17 General Electric Company Thermal actuated valve for clearance control
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
US4019320A (en) * 1975-12-05 1977-04-26 United Technologies Corporation External gas turbine engine cooling for clearance control
GB2111129A (en) * 1980-10-21 1983-06-29 Rolls Royce Mounting arrangement for a stage of stator blades for a gas turbine engine
GB2110306B (en) * 1981-11-26 1985-02-13 Roll Royce Limited Turbomachine housing
GB2115487B (en) * 1982-02-19 1986-02-05 Gen Electric Double wall compressor casing
JPH041309U (fr) * 1990-04-19 1992-01-08

Also Published As

Publication number Publication date
DE3509193A1 (de) 1986-09-25
EP0217837A1 (fr) 1987-04-15
US4778337A (en) 1988-10-18
WO1986005546A1 (fr) 1986-09-25
DE3661281D1 (en) 1988-12-29
JPS62502207A (ja) 1987-08-27

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