EP1721064B1 - Structure annulaire en construction metallique avec garniture d'admission - Google Patents

Structure annulaire en construction metallique avec garniture d'admission Download PDF

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Publication number
EP1721064B1
EP1721064B1 EP05715035A EP05715035A EP1721064B1 EP 1721064 B1 EP1721064 B1 EP 1721064B1 EP 05715035 A EP05715035 A EP 05715035A EP 05715035 A EP05715035 A EP 05715035A EP 1721064 B1 EP1721064 B1 EP 1721064B1
Authority
EP
European Patent Office
Prior art keywords
wall
metal
ring
ring structure
structure according
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 - Fee Related
Application number
EP05715035A
Other languages
German (de)
English (en)
Other versions
EP1721064A1 (fr
Inventor
Manfred A. DÄUBLER
Ulrike Hain
Werner Humhauser
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 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 Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1721064A1 publication Critical patent/EP1721064A1/fr
Application granted granted Critical
Publication of EP1721064B1 publication Critical patent/EP1721064B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00Manufacture
    • F05D2230/20Manufacture essentially without removing material
    • F05D2230/23Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/236Diffusion bonding
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00Manufacture
    • F05D2230/20Manufacture essentially without removing material
    • F05D2230/23Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237Brazing
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00Manufacture
    • F05D2230/20Manufacture essentially without removing material
    • F05D2230/23Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238Soldering
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/20Three-dimensional
    • F05D2250/28Three-dimensional patterned
    • F05D2250/283Three-dimensional patterned honeycomb
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00Materials; Properties thereof
    • F05D2300/60Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/601Fabrics

Definitions

  • the invention relates to a ring structure in metal construction according to the preamble of patent claim 1.
  • the wall structure should initially be sufficiently dimensionally stable and geometrically accurate. Thermal and mechanical influences should change the geometry as little as possible. Essentially, only the inside of the structure should be exposed to the usually hot working gas, leakage losses through the structure should be minimized. In steady-state operation, it is advantageous if the particular thermally induced dimensional change of the wall structure are adjusted in terms of time and size to those of the bladed rotor. Since mechanical contacts between the blade tips and the wall structure can hardly be avoided under special loads, the inside of the wall structure should at least be designed to be deformable on the point of the blade tip or resilient or capable of running.
  • the DE 100 20 673 C2 discloses a ring structure in metal construction for the blade area of axially flowed compressor and turbine stages.
  • the ring structure disclosed therein has an annular outer wall, which is designed as a closed, mechanically stable housing wall of the compressor or turbine stage.
  • the ring structure disclosed therein comprises an inner wall of annular shape and a connecting structure designed as a hollow chamber structure, wherein the connecting structure formed as a hollow chamber structure is sandwiched between the outer wall and the inner wall.
  • the connecting structure formed as a hollow chamber structure is connected on the one hand to the outer wall and on the other hand to the inner wall.
  • the annulus structure according to DE 100 20 673 C2 has an inner wall which is repeatedly interrupted over its circumference by axially or predominantly axially extending expansion joints.
  • Such an inner wall segmented by expansion joints has the disadvantage that flow losses can occur. Furthermore, increased by such a segmented inner wall, the complexity of the ring structure and thus the assembly and manufacturing costs. In addition, flaking, erosion or erosion damage may occur at the edges of the expansion joints during operation, causing the flow losses to increase again.
  • the DE 198 28 065 A1 relates to a honeycomb seal, in particular for a gas turbine, comprising a base plate, an air-evacuated honeycomb structure section (2), an intermediate plate (3) and a squealer section (4).
  • the abrading section (4) ie the inlet lining, may be embodied, inter alia, as metal felt.
  • the intermediate plate (3) is used to seal the evacuated honeycomb structure section (2). That is the hollow chamber structure, and forms a support for the abrading portion (4), for example for the metal felt.
  • the object of the present invention is to create a ring structure in metal construction which has a simplified construction.
  • This object is achieved by a ring structure in metal construction according to claim 1.
  • the inner wall is formed as a closed and mechanically stable structure of a metal fabric and / or a metal felt.
  • Fig. 1 and 2 show a first embodiment of a ring structure 10 according to the invention, wherein Fig. 2 the detail II of the Fig. 1 on an enlarged scale.
  • the ring structure 10 of the embodiment of Fig. 1 and 2 includes a circular outer wall 11, a circular inner wall 12 and a sandwiched between the outer wall 11 and the inner wall 12 connecting structure 13.
  • the outer wall 11 is formed as a closed, mechanically stable housing wall of a compressor stage or turbine stage of a gas turbine, in particular an aircraft engine.
  • the connecting structure 13 positioned between the outer wall 11 and the inner wall 12 is formed as a hollow chamber structure.
  • the hollow chamber structure 13 may have hexagonal, rectangular or even round chambers in cross-section in a cutting direction parallel to the inner wall or outer wall of the ring structure 10 in cross-section. In cross-section hexagonal chambers one speaks of a so-called honeycomb structure.
  • the inner wall 12 is formed as a closed and mechanically stable structure.
  • the inner wall 12 serves on the one hand for the mechanical stabilization of the ring structure 10 and on the other hand as an inlet lining for rotor blades (not shown) of rotating blades.
  • the internal wall 12 formed as a self-contained structure in the sense of the present invention is formed from a metal mesh and / or a metal felt.
  • a metal mesh is a structure in which metallic fibers or threads run systematically structured.
  • a metal felt is a structure in which metallic fibers are randomly or stochastically aligned.
  • the term metal mesh should also be understood to mean a knitted fabric made from metal fibers.
  • the formed as a closed structure inner wall 12 has characterized a simple construction.
  • connection structure 13 can be soldered to the inner wall 12 and the outer wall 11. Furthermore, it is possible to connect the connection structure 13 with the inner wall 12 and the outer wall 11, for example by so-called surface diffusion welding or by sintering.
  • the outer wall 11, the inner wall 12 and the connecting structure 13 are therefore connected to a total structure, namely to the ring structure 10 according to the invention, firmly together.
  • the inner wall 12 serves on the one hand to mechanically stabilize the ring structure 10 according to the invention and on the other hand as an inlet lining.
  • the inner wall 12 or the metal fabric and / or the metal felt of the inner wall 12 is made of a material which is resistant to oxidation at high temperatures.
  • the metal mesh or the metal felt for example, be made of a metal alloy based on a nickel material, iron material or cobalt material.
  • the metal mesh or the metal felt is joined together to form at least one joint to the annular inner wall 12.
  • a joint 14 of two mutually contacting edges of the metal fabric or metal felt for providing the inner wall 12 in the embodiment of the Fig. 2 the edges of the joint 14 extend in the radial direction, so that the two edges touch each other in the region of the joint 14, but no overlap occurs.
  • Fig. 3 to 6 show two further embodiments of inventive ring structures 15 and 16.
  • the embodiments of the Fig. 3 to 6 differ from the embodiment of Fig. 1 and 2
  • the exemplary embodiments are identical, so that the same reference numerals are used to avoid unnecessary repetitions for the same components.
  • a joint 17 which extends obliquely to the radial direction, that extends on the one hand in the radial direction and on the other hand in the circumferential direction of the ring structure 15.
  • a shock point 17 formed in this way an overlap of the corresponding edges takes place without material thickening.
  • FIGS. 5 and 6 show an embodiment of a ring structure 16 according to the invention, in which a shock point 18 is present in the region of the inner wall 12, in which abutting edges to form a material thickening 19 overlap each other.
  • the material thickening 19 is directed radially outward, the material thickening 19 thus extends into the region of the connecting structure 13 inside.
  • the chambers of the connecting structure 13 can be shortened accordingly in the region in which the material thickening 19 extends.
  • a metallic ring structure is proposed in which the inner wall is closed and further made of a metal mesh and / or a metal felt. Due to the closed structure of the inner wall flow losses can be minimized. By using the metal mesh or metal felt thermal strains can be intercepted without cracking. As a result, a much simpler construction of a ring structure is possible.
  • the inner wall of the metal felt or metal fabric continues to serve as inlet lining.

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

Claims (10)

  1. Structure annulaire en construction métallique pour une zone d'aubes mobiles dans des étages de compresseur et de turbine, traversés dans la direction axiale, en particulier dans des turbines à gaz, comportant une paroi extérieure (11) annulaire, une paroi intérieure (12) annulaire et située à faible distance radiale des pointes des aubes mobiles, et comportant une structure de liaison (13), réalisée sous forme de structure à chambres creuses, disposée entre la paroi extérieure (11) et la paroi intérieure (12), ladite paroi extérieure (11) étant réalisée sous la forme d'une paroi fermée, mécaniquement stable de l'étage du compresseur ou de la turbine, la structure de liaison (13), réalisée sous forme de structure à chambres creuses, étant reliée à la paroi extérieure (11) et à la paroi intérieure (12), et ladite paroi intérieure (12) formant une garniture d'admission pour les pointes des aubes mobiles, caractérisée en ce que la paroi intérieure (12) est réalisée en totalité sous forme de structure fermée et mécaniquement stable en textile métallique et/ou en feutre métallique.
  2. Structure annulaire selon la revendication 1, caractérisée en ce que le textile métallique et/ ou le feutre métallique sont formés par un alliage métallique résistant à l'oxydation sous des températures élevées, en particulier un alliage à base de fer, de nickel ou de cobalt.
  3. Structure annulaire selon la revendication 1 ou 2, caractérisée en ce que le textile métallique et/ou le feutre métallique forment la paroi intérieure (12) annulaire, fermée en soi, ledit textile métallique et/ou ledit feutre métallique étant réunis en formant au moins une zone de joint (14 ; 17 ; 18) dans la paroi intérieure (12).
  4. Structure annulaire selon la revendication 3, caractérisée en ce que la ou chaque zone de joint (17 ; 18) est formée par respectivement deux bords face à face, lesdits bords se chevauchant de préférence.
  5. Structure annulaire selon la revendication 4, caractérisée en ce que les bords se chevauchent l'un l'autre sans former un épaississement de matière.
  6. Structure annulaire selon la revendication 4, caractérisée en ce que les bords se chevauchent l'un l'autre en formant un épaississement de matière (19), ledit épaississement de matière (19) étant orienté radialement vers l'extérieur en direction de la structure de liaison (13) réalisée sous forme de structure à chambres creuses.
  7. Structure annulaire selon l'une quelconque des revendications 1 à 6, caractérisée en ce que la paroi intérieure (12), réalisée dans le textile métallique et/ou le feutre métallique est assemblée de manière fixe, par frittage ou soudage par diffusion superficielle, à la structure de liaison (13), réalisée sous forme de structure à chambres creuses.
  8. Structure annulaire selon la revendication 7, caractérisée en ce que la structure de liaison (13), réalisée sous forme de structure à chambres creuses est assemblée de manière fixe, par frittage ou soudage par diffusion superficielle, à la paroi extérieure (11).
  9. Structure annulaire selon l'une quelconque des revendications 1 à 8, caractérisée en ce que la paroi intérieure (12), réalisée dans le textile métallique et/ou le feutre métallique est assemblée de manière fixe par brasage à la structure de liaison (13), réalisée sous forme de structure à chambres creuses.
  10. Structure annulaire selon la revendication 9, caractérisée en ce que la structure de liaison (13), réalisée sous forme de structure à chambres creuses est assemblée de manière fixe par brasage à la paroi extérieure (11).
EP05715035A 2004-03-03 2005-02-28 Structure annulaire en construction metallique avec garniture d'admission Expired - Fee Related EP1721064B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004010236A DE102004010236A1 (de) 2004-03-03 2004-03-03 Ringstruktur in Metallbauweise
PCT/DE2005/000333 WO2005085600A1 (fr) 2004-03-03 2005-02-28 Structure annulaire en construction metallique avec garniture d'admission

Publications (2)

Publication Number Publication Date
EP1721064A1 EP1721064A1 (fr) 2006-11-15
EP1721064B1 true EP1721064B1 (fr) 2010-06-02

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP05715035A Expired - Fee Related EP1721064B1 (fr) 2004-03-03 2005-02-28 Structure annulaire en construction metallique avec garniture d'admission

Country Status (4)

Country Link
US (1) US8061965B2 (fr)
EP (1) EP1721064B1 (fr)
DE (2) DE102004010236A1 (fr)
WO (1) WO2005085600A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2495399B1 (fr) * 2011-03-03 2016-11-23 Safran Aero Booster S.A. Virole externe segmentée apte à compenser un désalignement du rotor par rapport au stator
ES2705532T3 (es) 2012-10-30 2019-03-25 MTU Aero Engines AG Anillo de turbina y turbomáquina
US10472980B2 (en) * 2017-02-14 2019-11-12 General Electric Company Gas turbine seals
TR201705399A2 (tr) * 2017-04-11 2017-09-21 Sdm Siradisi Arge Ve Muehendislik Sanayi Ticaret Anonim Sirketi Örgü kumaş destekli yaprak keçe
DE102017211316A1 (de) 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring

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US3126149A (en) * 1964-03-24 Foamed aluminum honeycomb motor
US3042365A (en) * 1957-11-08 1962-07-03 Gen Motors Corp Blade shrouding
US3068016A (en) * 1958-03-31 1962-12-11 Gen Motors Corp High temperature seal
US3056583A (en) * 1960-11-10 1962-10-02 Gen Electric Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US3053694A (en) * 1961-02-20 1962-09-11 Gen Electric Abradable material
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US3425665A (en) * 1966-02-24 1969-02-04 Curtiss Wright Corp Gas turbine rotor blade shroud
US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal
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US4135851A (en) * 1977-05-27 1979-01-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
US4409054A (en) * 1981-01-14 1983-10-11 United Technologies Corporation Method for applying abradable material to a honeycomb structure and the product thereof
GB2095749B (en) * 1981-03-25 1984-12-12 Rolls Royce Gas turbine engine having improved resistance for foreign object ingestion damage
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JP4285134B2 (ja) * 2003-07-04 2009-06-24 株式会社Ihi シュラウドセグメント

Also Published As

Publication number Publication date
EP1721064A1 (fr) 2006-11-15
DE502005009677D1 (de) 2010-07-15
US8061965B2 (en) 2011-11-22
DE102004010236A1 (de) 2005-09-15
WO2005085600A1 (fr) 2005-09-15
US20090263239A1 (en) 2009-10-22

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