EP2719867A1 - Structure de boîtier avec étanchéification et refroidissement améliorés - Google Patents

Structure de boîtier avec étanchéification et refroidissement améliorés Download PDF

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Publication number
EP2719867A1
EP2719867A1 EP12188313.6A EP12188313A EP2719867A1 EP 2719867 A1 EP2719867 A1 EP 2719867A1 EP 12188313 A EP12188313 A EP 12188313A EP 2719867 A1 EP2719867 A1 EP 2719867A1
Authority
EP
European Patent Office
Prior art keywords
housing wall
housing structure
structure according
web
heat shield
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
Application number
EP12188313.6A
Other languages
German (de)
English (en)
Other versions
EP2719867B1 (fr
Inventor
Manfred Feldmann
Janine Dr. Sangl
Sebastian Kaltenbach
Joachim Lorenz
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 Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP12188313.6A priority Critical patent/EP2719867B1/fr
Priority to ES12188313.6T priority patent/ES2531468T3/es
Priority to US14/052,338 priority patent/US9416672B2/en
Publication of EP2719867A1 publication Critical patent/EP2719867A1/fr
Application granted granted Critical
Publication of EP2719867B1 publication Critical patent/EP2719867B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F05D2240/15—Heat shield

Definitions

  • the present invention relates to a housing structure for a turbomachine, in particular for a gas turbine or an aircraft engine.
  • turbomachines such as gas turbines or aircraft engines
  • air is drawn along a flow channel, compressed, and combusted in a combustion chamber along with fuel, and then the combustion gases are discharged through the flow channel, thereby driving in a turbine rotors.
  • the flow channel is circumferentially surrounded by a housing structure, wherein in the region of the combustion chamber and the following turbine, by the combustion gases very high temperatures prevail in the flow channel, so that surrounding the flow channel housing structure must be efficiently cooled in order to achieve that the lowest possible operating temperatures are present in order to use materials with lower requirements for high-temperature properties.
  • cooling air is passed into the area of the outer housing structure in order to bring about heat dissipation.
  • insulators and heat shields are used in such housing structures to protect the outer components from excessive temperatures.
  • the invention is based on the recognition that the existing in the prior art recesses in the field of heat shields or generally the presence of openings in the region of bushings in the radial direction causes inadmissible amount of hot gas can flow into the outer region of the housing structure.
  • the invention therefore provides for placing a seal in the region in which the heat shield is interrupted, so that hot gas is prevented from flowing in the direction of the outer housing structure.
  • it is proposed to be provided on webs or brackets which are arranged on an inner housing wall and at least partially in the radial direction outwardly, such as. to guide vane webs or Leitschaufelhalterept to provide broadening and form at these widening sealing surfaces against which heat shields sealingly so as to achieve a seal.
  • Broadening is here understood to mean an enlargement of the cross section of a web or a holder in at least one direction, which extends in particular in a direction transverse to the radial direction, whereby a new cross-sectional reduction is preferably provided in addition to the cross-sectional enlargement, so that the broadening only in a certain Section of the web or the bracket is present.
  • the broadening on a web or a holder of the inner housing wall may in particular be made in one piece, so that additional mounting components and additional assembly costs can be saved.
  • the broadening can be cast on a corresponding web or a holder.
  • At least one widening may be provided on a web circulating circumferentially about the flow channel or a corresponding support of the inner housing wall on opposite sides facing away from each other, on each of which a heat shield sealingly abuts, so that both in the axial direction as well as in the circumferential direction as closed as possible barrier wall of heat shields for the separation of an outer part of the housing structure is formed with outer cavities of an inner part of the housing structure with internal cavities.
  • the inner and outer cavities may have corresponding cooling air inlet openings to allow for inflow of cooling air.
  • the attached figure shows in a purely schematic way a partial sectional view of a housing structure according to the invention.
  • the attached figure shows a section of a housing structure according to the invention with an outer housing wall 1, which can be designed segmented both in the axial direction and circulate around the limited of its flow channel.
  • a guide blade 3 is arranged, which forms a part of the inner housing wall 2 in the form of a shroud.
  • a guide blade web 4 is arranged projecting obliquely outwards, which can serve for example for fixing the guide vane 3 to the outer housing wall 1.
  • heat shields are provided 6.7, which are also at least partially formed circumferentially around the flow channel and to shield the outer housing wall 1 from the temperatures in the flow channel.
  • the heat shields 6 and 7 limit in the embodiment shown both inner cavities 9, as well as outer cavities 10th
  • the outer cavities 10 are limited not only by the heat shields 6,7, but also by the outer housing wall 1 and the Leitschaufelsteg 4.
  • cooling air openings 11 are partially provided, which allow to direct air from the environment into the outer cavities 10 in order to provide a cooling effect for the housing with respect to the high temperatures in the flow channel.
  • the heat shields 6.7 continue to limit internal cavities 9, which are largely separated from the outer cavities 10 and sealed.
  • a sealing surface 8 is provided, which is in contact with the heat shield 7 and 6, respectively, to seal the inner cavities 8 and outer cavities 10.
  • the inner cavities 9 are spaced from the outer housing wall 1 and the outer cavities 10 are spaced from the inner housing wall 2, so that the inner cavities 9 serve as a temperature buffer, while the outer cavities 10 can be used to guide cooling air.
  • the outer housing wall 1 and the components in the region of the outer housing wall 1 can be effectively cooled and the temperature load can be lowered, so that materials can be used with lower requirements for temperature resistance.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12188313.6A 2012-10-12 2012-10-12 Structure de boîtier avec étanchéification et refroidissement améliorés Not-in-force EP2719867B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP12188313.6A EP2719867B1 (fr) 2012-10-12 2012-10-12 Structure de boîtier avec étanchéification et refroidissement améliorés
ES12188313.6T ES2531468T3 (es) 2012-10-12 2012-10-12 Estructura de caja con obturación y refrigeración mejoradas
US14/052,338 US9416672B2 (en) 2012-10-12 2013-10-11 Housing structure with improved seal and cooling

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12188313.6A EP2719867B1 (fr) 2012-10-12 2012-10-12 Structure de boîtier avec étanchéification et refroidissement améliorés

Publications (2)

Publication Number Publication Date
EP2719867A1 true EP2719867A1 (fr) 2014-04-16
EP2719867B1 EP2719867B1 (fr) 2015-01-21

Family

ID=47115341

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12188313.6A Not-in-force EP2719867B1 (fr) 2012-10-12 2012-10-12 Structure de boîtier avec étanchéification et refroidissement améliorés

Country Status (3)

Country Link
US (1) US9416672B2 (fr)
EP (1) EP2719867B1 (fr)
ES (1) ES2531468T3 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10557364B2 (en) * 2016-11-22 2020-02-11 United Technologies Corporation Two pieces stator inner shroud

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020122716A1 (en) * 2001-02-28 2002-09-05 Beacock Robert John Methods and apparatus for cooling gas turbine engine blade tips
EP1384858A2 (fr) * 2002-07-26 2004-01-28 General Electric Company Refroidissement de la surface intérieure de l'enveloppe de stateur dans la section basse pression d'une turbine à gaz
US20070231123A1 (en) * 2006-03-30 2007-10-04 Snecma Device for cooling a turbomachine turbine casing

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2800797B1 (fr) 1999-11-10 2001-12-07 Snecma Assemblage d'un anneau bordant une turbine a la structure de turbine
FR2803871B1 (fr) * 2000-01-13 2002-06-07 Snecma Moteurs Agencement de reglage de diametre d'un stator de turbine a gaz
GB0619426D0 (en) * 2006-10-03 2006-11-08 Rolls Royce Plc A vane arrangement
FR2968030B1 (fr) * 2010-11-30 2013-01-11 Snecma Turbine basse-pression de turbomachine d'aeronef, comprenant un distributeur sectorise
US8876458B2 (en) * 2011-01-25 2014-11-04 United Technologies Corporation Blade outer air seal assembly and support
US8985944B2 (en) * 2011-03-30 2015-03-24 General Electric Company Continuous ring composite turbine shroud

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020122716A1 (en) * 2001-02-28 2002-09-05 Beacock Robert John Methods and apparatus for cooling gas turbine engine blade tips
EP1384858A2 (fr) * 2002-07-26 2004-01-28 General Electric Company Refroidissement de la surface intérieure de l'enveloppe de stateur dans la section basse pression d'une turbine à gaz
US20070231123A1 (en) * 2006-03-30 2007-10-04 Snecma Device for cooling a turbomachine turbine casing

Also Published As

Publication number Publication date
ES2531468T3 (es) 2015-03-16
US9416672B2 (en) 2016-08-16
EP2719867B1 (fr) 2015-01-21
US20140102107A1 (en) 2014-04-17

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