EP1766194A1 - Systeme de garniture d'etancheite et procede de production d'un corps d'etancheite pour un systeme de garniture d'etancheite - Google Patents

Systeme de garniture d'etancheite et procede de production d'un corps d'etancheite pour un systeme de garniture d'etancheite

Info

Publication number
EP1766194A1
EP1766194A1 EP05763723A EP05763723A EP1766194A1 EP 1766194 A1 EP1766194 A1 EP 1766194A1 EP 05763723 A EP05763723 A EP 05763723A EP 05763723 A EP05763723 A EP 05763723A EP 1766194 A1 EP1766194 A1 EP 1766194A1
Authority
EP
European Patent Office
Prior art keywords
sealing
wear
sealing arrangement
base body
arrangement 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.)
Withdrawn
Application number
EP05763723A
Other languages
German (de)
English (en)
Inventor
Horst Pillhöfer
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 EP1766194A1 publication Critical patent/EP1766194A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
    • C23C26/02—Coating not provided for in groups C23C2/00 - C23C24/00 applying molten material to the substrate
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/02—Pretreatment of the material to be coated
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/12—Preventing 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
    • F01D11/122—Preventing 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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/132—Chromium
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining

Definitions

  • the invention relates to a sealing arrangement according to the preamble of patent claim 1 and a method for producing a sealing body for a sealing arrangement according to the preamble of patent claim 10.
  • the invention further relates to a turbomachine and a gas turbine.
  • Gas turbines consist of several modules, such. B. from at least ei ⁇ NEM compressor, a combustion chamber and at least one turbine.
  • the or each compressor and the or each turbine have a rotor which rotates with respect to a stationary stator.
  • the stator is a stationary housing, to which fixed guide vanes are assigned.
  • Rotor blades are assigned to the rotor, which blades rotate together with the rotor relative to the stationary guide vanes and the stationary housing.
  • sealing systems for minimizing leakage flows between the rotating rotor and the stationary stator.
  • a gap must be sealed between radially inner ends of the fixed guide vanes and the rotating rotor.
  • a seal arrangement for sealing the gap between the radially inward ends of the stationary vanes and the rotating rotor is also referred to as “inner air seal.”
  • Another gap to be sealed is, for example, between the radially outer ends of the rotating blades and the fixed one
  • a sealing arrangement for sealing the gap between the radially outer ends of the rotating rotor blades and the housing is also referred to as the "Outer Air Seal".
  • sealing arrangements for providing a so-called “inner air seal” or “outer air seal” as labyrinth seals, such labyrinth seals being composed of a first porous sealing body and a first sealing body cooperating with the first sealing body. be formed cut-shaped second sealing body ge.
  • the first, porous sealing body can be designed, for example, as a honeycomb sealing body.
  • the first Form sealing body as a porous material layer.
  • the cooperating with the first sealing body, cutting-shaped, second sealing body is also referred to as Dichtfin.
  • the sealing fins are preferably associated with the rotor or rotating blades in the region of an outer shroud thereof.
  • the porous sealing body is preferably assigned to the housing or the stationary guide vanes in the region of an inner cover band of the same.
  • labyrinth sealing systems are suitable for high temperatures which are sustained above 500 0 C, not suitable because die ⁇ same at high operating temperatures a large wear are exposed by for example oxidation. Furthermore, they are subject to vibrational stress or strain. Accordingly, labyrinth seals known from the prior art have a limited service life at temperatures above 500 ° C. Due to the increasing optimization of gas turbines, however, increasingly higher operating temperatures occur within the same, so that the labyrinth seals known from the prior art must be improved.
  • the present invention is based on the problem to provide a novel seal assembly and a method for producing ei ⁇ Nes sealing body for a seal assembly.
  • the or each first sealing body has a base body and a porous wear body, wherein the base body and the wearing body have a graded material composition.
  • the porous sealing body consists of a base body and a porous wear body, wherein the base body and the porous wear body aufwei ⁇ a graded material composition aufwei ⁇ sen.
  • the main body and the porous wear body preferably have a degree of aluminum and / or chromium in the region of their surfaces.
  • the oxidation resistance of the wear body and body is significantly improved, so that the seal assemblies can be used even at temperatures above 600 0 C.
  • the rigidity of the component is increased and at the same time the ductility of the porous wear body is maintained.
  • the base body and the wear body have an aluminum content of 15% by weight to 35% by weight in the region of their surfaces or edge zones.
  • the inventive method for producing a sealing body for ei ⁇ ne seal arrangement is defined in claim 10.
  • the method comprises at least the following steps: a) provision of a base body; b) providing a porous wear body; c) connecting the main body and the wear body; d) Alitating and / or crushing interconnected base body and wear body.
  • Figure 1 is a schematic section of a seal assembly according to the invention.
  • FIG. 2 shows a detail of the seal arrangement according to FIG. 1;
  • FIG. 3 shows an alternative detail of the sealing arrangement according to FIG. 1; FIG. and
  • Fig. 4 is a schematic section of another erfindungs ⁇ contemporary seal assembly.
  • FIG. 1 shows a sealing arrangement 10 according to a first embodiment of the invention for sealing a gap 11 between a rotor 12 and a stator 13 of a gas turbine, in particular a low-pressure turbine of an aircraft engine.
  • the sealing arrangement 10 illustrated in FIG. 1 may be, for example, a so-called "outer air seal", in which case the stator 13 is surrounded by a housing and the rotor 12 by rotating rotor blades, namely an outer shroud of the rotor blades. is formed.
  • FIG. 1 The sealing arrangement of FIG. 1 is formed by a first sealing body 14 associated with the stator 13 and a second sealing body 15 cooperating with the first sealing body 14.
  • Fig. 2 shows the first sealing body 14 in isolation.
  • the first sealing body 14 is formed by a support body or base body 16 and a porous wear body 17.
  • the main body 16 and the wear body 17 are firmly connected to one another, for example, by high-temperature soldering.
  • the porous wear body 17 is formed as a honeycomb seal body.
  • 3 shows an alternative embodiment of the first sealing body 14, in which the porous wear body 17 is formed of a porous material layer, in particular of a metal powder sintered body.
  • the base body 16 and the porous wear body 17 are each formed from an iron-based alloy or a nickel-based alloy, which have a graded material composition in the region of their surfaces or edge zones with respect to aluminum and / or chromium.
  • the aluminum content and / or chromium content in the region of the surface or edge zone of base body 16 and wear body 17 is in a range between 15% by weight and 35% by weight. This results in the area of the surfaces or marginal zones an intermetallic alloy composition for applications at temperatures of more than 600 0 C be ⁇ sitting optimized oxidation resistance.
  • FIG. 4 shows a further sealing arrangement 18 according to the invention, which substantially corresponds to the exemplary embodiment of FIG. 1. Therefore, like reference numerals are used for the same assemblies.
  • the sealing arrangement 18 of FIG. 4 differs from the sealing arrangement 10 according to FIG. 1 only in that the wear body 17 is graduated and cooperates with two second, blade-shaped sealing bodies 15 which have a different radial extent. With regard to the remaining details, however, reference may be made to the above statements.
  • the procedure is such that first a base body 16 and a porous wear body 17 are provided for the sealing arrangements, the base body and the wear body being made of an iron-based alloy or a nickel-based alloy tion are made.
  • the porous wear body 17 may be a honeycomb seal body or a sealing body made of a porous material layer, in particular a metal powder sintered body.
  • the wear body 17 and the base 16 are firmly connected.
  • the bonding of the main body 16 to the wear body 17 preferably takes place by high-temperature soldering under vacuum, wherein the soldering temperature is greater than approximately 80% of the melting temperature of the base material of the wear body 17 to be joined together and the base body 16.
  • a wear body 17 made of Hastalloy honeycomb structure, so the soldering temperature may be, for example, 1180 0 C.
  • the joining of wear body 17 and base body 16 can also be effected by diffusion bonding.
  • Alitizing and / or chromating is preferably carried out by means of a chemical vapor deposition (CVD) process, wherein the Alitieren and / or chromium on the surface or at the edge zone of the base body 16 and porous wear body 17 a Legie ⁇ rungsgradient with respect to aluminum and / or chrome. Preferred wise one aluminizing at 1050 0 C by four hours.
  • CVD chemical vapor deposition
  • the sealing arrangement according to the invention is preferably used in turbomachines, gas turbines or aircraft engines. It is suitable in particular for use in a low-pressure turbine of an aircraft engine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un système de garniture d'étanchéité pour turbomachine, pour étanchéifier une fente (111) située entre un rotor (12) et un stator (13), qui comprend au moins un premier corps d'étanchéité (14) associé de préférence au stator et au moins un second corps d'étanchéité (15) à arête coupante, associé de préférence au rotor et coopérant avec le premier ou chacun des premiers corps d'étanchéité (14). Selon l'invention, le ou chaque premier corps d'étanchéité (14) présente un corps de base (16) et un corps d'usure (17) poreux. Le corps de base (16) et le corps d'usure (17) présentent une composition de matériau graduée.
EP05763723A 2004-07-15 2005-07-05 Systeme de garniture d'etancheite et procede de production d'un corps d'etancheite pour un systeme de garniture d'etancheite Withdrawn EP1766194A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004034312A DE102004034312A1 (de) 2004-07-15 2004-07-15 Dichtungsanordnung und Verfahren zur Herstellung eines Dichtkörpers für eine Dichtungsanordnung
PCT/DE2005/001177 WO2006005308A1 (fr) 2004-07-15 2005-07-05 Systeme de garniture d'etancheite et procede de production d'un corps d'etancheite pour un systeme de garniture d'etancheite

Publications (1)

Publication Number Publication Date
EP1766194A1 true EP1766194A1 (fr) 2007-03-28

Family

ID=35094183

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05763723A Withdrawn EP1766194A1 (fr) 2004-07-15 2005-07-05 Systeme de garniture d'etancheite et procede de production d'un corps d'etancheite pour un systeme de garniture d'etancheite

Country Status (4)

Country Link
US (1) US20080258404A1 (fr)
EP (1) EP1766194A1 (fr)
DE (1) DE102004034312A1 (fr)
WO (1) WO2006005308A1 (fr)

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DE102007004743A1 (de) 2007-01-31 2008-08-07 Mtu Aero Engines Gmbh Dichtungsanordnung
US20090072487A1 (en) * 2007-09-18 2009-03-19 Honeywell International, Inc. Notched tooth labyrinth seals and methods of manufacture
DE102007047739B4 (de) * 2007-10-05 2014-12-11 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenverdichter mit Anlaufschicht
DE102009016803A1 (de) * 2009-04-09 2010-10-14 Rolls-Royce Deutschland Ltd & Co Kg Labyrinth-Anstreifdichtung für eine Strömungsmaschine
RU2498879C1 (ru) * 2012-08-01 2013-11-20 Общество с ограниченной ответственностью "Научно-производственное предприятие Вакууммаш" Составной сегмент прирабатываемого уплотнения турбины
EP2722486B1 (fr) * 2012-10-17 2016-12-07 MTU Aero Engines AG Support de joint d'étanchéité pour ensemble statorique
WO2015084441A2 (fr) * 2013-08-30 2015-06-11 United Technologies Corporation Joint d'étanchéité coulissant
US10240473B2 (en) 2013-08-30 2019-03-26 United Technologies Corporation Bifurcated sliding seal
WO2015034636A1 (fr) * 2013-09-06 2015-03-12 General Electric Company Ensemble joint stratifié pour turbine à gaz comprenant des première et seconde couches alvéolées et une plaque d'étanchéité intermédiaire perforée entre elles
EP2998517B1 (fr) * 2014-09-16 2019-03-27 Ansaldo Energia Switzerland AG Agencement d'étanchéité au niveau de l'interface entre une chambre de combustion et une turbine d'une turbine à gaz et turbine à gaz avec un tel agencement d'étanchéité
FR3055353B1 (fr) * 2016-08-25 2018-09-21 Safran Aircraft Engines Ensemble formant joint d'etancheite a labyrinthe pour une turbomachine comportant un abradable et des lechettes inclines
US10369630B2 (en) * 2017-02-24 2019-08-06 General Electric Company Polyhedral-sealed article and method for forming polyhedral-sealed article
US11674396B2 (en) 2021-07-30 2023-06-13 General Electric Company Cooling air delivery assembly
US11674405B2 (en) 2021-08-30 2023-06-13 General Electric Company Abradable insert with lattice structure

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Also Published As

Publication number Publication date
DE102004034312A1 (de) 2006-02-02
WO2006005308A1 (fr) 2006-01-19
US20080258404A1 (en) 2008-10-23

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