EP2001621A2 - Procédé de fabrication d'une garniture d'étanchéité en nid d'abeilles - Google Patents

Procédé de fabrication d'une garniture d'étanchéité en nid d'abeilles

Info

Publication number
EP2001621A2
EP2001621A2 EP07722126A EP07722126A EP2001621A2 EP 2001621 A2 EP2001621 A2 EP 2001621A2 EP 07722126 A EP07722126 A EP 07722126A EP 07722126 A EP07722126 A EP 07722126A EP 2001621 A2 EP2001621 A2 EP 2001621A2
Authority
EP
European Patent Office
Prior art keywords
cells
honeycomb
shaped body
injection molding
honeycomb seal
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Withdrawn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
EP07722126A
Other languages
German (de)
English (en)
Inventor
Reinhold Meier
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 EP2001621A2 publication Critical patent/EP2001621A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
    • B22F3/225—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip by injection molding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B28—WORKING CEMENT, CLAY, OR STONE
    • B28B—SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS; SHAPING SLAG; SHAPING MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER
    • B28B11/00—Apparatus or processes for treating or working the shaped or preshaped articles
    • B28B11/003—Apparatus or processes for treating or working the shaped or preshaped articles the shaping of preshaped articles, e.g. by bending
    • B28B11/006—Making hollow articles or partly closed articles
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B38/00—Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
    • C04B38/0006—Honeycomb structures
    • C04B38/0012—Honeycomb structures characterised by the material used for sealing or plugging (some of) the channels of the honeycombs
    • 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
    • F01D11/127—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 a deformable or crushable structure, e.g. honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B28—WORKING CEMENT, CLAY, OR STONE
    • B28B—SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS; SHAPING SLAG; SHAPING MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER
    • B28B3/00—Producing shaped articles from the material by using presses; Presses specially adapted therefor
    • B28B3/20—Producing shaped articles from the material by using presses; Presses specially adapted therefor wherein the material is extruded
    • B28B2003/203—Producing shaped articles from the material by using presses; Presses specially adapted therefor wherein the material is extruded for multi-channelled structures, e.g. honeycomb structures
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2111/00—Mortars, concrete or artificial stone or mixtures to prepare them, characterised by specific function, property or use
    • C04B2111/00474—Uses not provided for elsewhere in C04B2111/00
    • C04B2111/00982—Uses not provided for elsewhere in C04B2111/00 as construction elements for space vehicles or aeroplanes
    • 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

Definitions

  • the invention relates to a method for producing a honeycomb seal according to the preamble of claim 1.
  • titanium alloys The most important materials used today for aircraft engines or other gas turbines are titanium alloys, nickel alloys (also called superalloys) and high-strength steels.
  • the high strength steels are used for shaft parts, gear parts, compressor casings and turbine casings.
  • Titanium alloys are typical materials for compressor parts.
  • Nickel alloys are suitable for the hot parts of the aircraft engine.
  • As a manufacturing method for gas turbine components made of titanium alloys, nickel alloy or other alloys are known from the prior art primarily investment casting and forging. All highly stressed gas turbine components, such as components for a compressor, are forgings. Components for a turbine, however, are usually designed as precision castings.
  • Powder metallurgical injection molding represents an alternative for the manufacture or production of complex components.
  • Powder metallurgical injection molding is related to plastic injection molding and is also referred to as metal mold injection or metal injection molding (MIM-V experienced).
  • MIM-V metal mold injection or metal injection molding
  • With the powder metallurgical injection molding components can be produced, which reach almost the full density and approximately the static strength of forgings. As a rule, the reduced dynamic strength compared to forgings can be compensated for by suitable material selection. be siert.
  • the procedure is such that in a first process step a powder, preferably a metal powder and / or a ceramic powder, is mixed with a binder and optionally a plasticizer and optionally further additives to form a homogeneous mass. From this homogeneous mass, a molding for the honeycomb seal is made by injection molding.
  • the injection-molded body already has the geometric shape of the honeycomb seal to be produced and thus honeycomb-like cells, but its volume is increased by the volume of the binder and plasticizer added.
  • the injection-molded article is deprived of binder and plasticizer in a debinding process. Subsequently, during the sintering, the molded body is compressed or shrunk to the finished honeycomb seal.
  • honeycomb seals produced by powder metallurgical injection molding are suitable, for example, for sealing in a gas turbine a radially outer gap between blade tips of rotating blades and a stationary housing. If such honeycomb seals also assume a heat transfer function in addition to the sealing function, it is already known from practice to arrange a heat-insulating filling in the honeycomb cells of the finished honeycomb seal, this heat-insulating filling being firmly connected to the honeycomb seal by soldering. The soldering of heat-insulating fillings with the honeycomb cells of a honeycomb seal is technically particularly complex.
  • the present invention is based on the problem to provide a novel method for producing a honeycomb seal with fauxdärnmfunktion.
  • At least some of the cells of the molding are at least partially sintered before sintering. each filled with at least one hollow body, wherein then the shaped body is sintered together with the introduced into the cells hollow bodies.
  • heat-insulating hollow bodies at least in each case one heat-insulating hollow body in at least some of the cells of the shaped body before sintering a shaped body of a honeycomb seal to be produced by powder metallurgical injection molding.
  • the heat-curable hollow bodies are firmly connected to the honeycomb cells of the molded body.
  • soldering of heat-insulating fillings with the cells of the honeycomb seal can be dispensed with, resulting in a particularly efficient manufacturing process for honeycomb seals with a thermal insulation function.
  • the present invention relates to the production of a honeycomb seal by powder metallurgical injection molding.
  • Powder metallurgy injection molding is also referred to as Metal Injection Molding (MIM).
  • MIM Metal Injection Molding
  • the procedure is such that a metal powder and / or a ceramic powder is provided in a first step.
  • a binder and optionally a plasticizer and optionally further additives are provided in a second step.
  • the provided metal powder and / or ceramic powder and the provided binder and optionally the plasticizer and optionally the other additives are mixed in a third step, so that forms a homogeneous mass.
  • the volume fraction of the metal powder and / or ceramic powder in the homogeneous mass is preferably between 50% and 70%.
  • the proportion of binder and optionally plasticizer on the homogeneous mass varies approximately between 30% and 50%.
  • This homogeneous mass of metal powder and / or ceramic powder, binder and optionally plasticizer is then further processed by injection molding in a further process step.
  • injection molding a shaped body of the honeycomb seal to be produced is manufactured.
  • This shaped body already has all the typical features of the honeycomb seal to be produced.
  • the shaped body has the geometric shape of the honeycomb seal to be produced, that is to say honeycomb-like cells.
  • the molded article has a volume increased by the binder content and plasticizer content.
  • the moldings provided by injection molding are also called greenware.
  • the binder and the plasticizer is expelled from the molding.
  • This step can also be called a de-bonding process.
  • the expulsion of binder and plasticizer can be done in different ways. This is usually done by fractional, thermal decomposition or evaporation. Another possibility consists of sucking out the thermally liquefied binding and plasticizing agents by capillary forces, by sublimation or by solvents.
  • the shaped body after the debindering process is also called browning.
  • the shaped body is sintered. During the sintering, the shaped body is compacted to the honeycomb seal with the final geometric properties. During sintering, therefore, the shaped body decreases, wherein the dimensions of the shaped body must uniformly decrease in all three spatial directions. The linear shrinkage is dependent on the binder content and plasticizer content between 10% and 20%.
  • the sintering can be carried out under different protective gases or under vacuum. After sintering, the finished honeycomb seal is present. If necessary, after the sintering, the honeycomb seal can be subjected to a refining process. However, the refining process is optional. nal. It can already be present immediately after sintering a ready-to-install honeycomb seal.
  • the heat-insulating hollow body with the honeycomb cells of the molded body enter a firm connection.
  • the heat-insulating hollow bodies are preferably introduced before the debinding process into the cells of the green body, still soft molded body.
  • the honeycomb cells of the molding are at least partially filled with at least one heat-insulating hollow body. It is therefore possible to introduce in each honeycomb cell of the molding exclusively a heat-insulating hollow body. It is also possible to introduce in each honeycomb cell a plurality of heat-insulating hollow body. By filling the honeycomb cells with at least one hollow body, they may be filled either partially or completely by the or each thermally insulating hollow body.
  • a homogeneous mass is used for injection molding of the shaped body of the honeycomb seal to be produced, which was obtained using a metal powder, metallic or metallized hollow body are used as a heat-insulating hollow body.
  • Metallized hollow bodies are those hollow bodies which are metallically coated on their outer surface.
  • ceramic bodies or hollow bodies ceramized on its outer surface are used as hollow bodies.
  • they may optionally be provided on their outer surface with a slip layer.
  • the heat-insulating hollow bodies to be introduced into the honeycomb cells of the shaped body are preferably adapted in size and shape to the honeycomb-like cells of the shaped body.
  • Particularly preferably hollow bodies designed as hollow spheres are used, which are pressed into the honeycomb cells of the shaped body.
  • the honeycomb cells of the shaped body may have different geometric shapes, e.g. round, oval or even polygonal, in particular hexagonal, be contoured.
  • honeycomb seal By filling the honeycomb cells of a molded article produced by injection molding for a honeycomb seal before sintering the same with hollow bodies, a honeycomb seal with thermal insulation function can be produced in a particularly simple manner. By filling the honeycomb cells with the hollow bodies, the sealing effect of the honeycomb seal is further improved. Furthermore, when rubbing blade tips of rotating blades into the honeycomb seal, the abrasion thereof is reduced, so that it has a longer service life.
  • the hollow bodies are subcooled before they are imported into the honeycomb cells of the molded body, ie cooled to a temperature which is lower than the temperature of the shaped body. This can avoid that the honeycomb cells are damaged during insertion of the hollow body.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Ceramic Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • General Engineering & Computer Science (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Powder Metallurgy (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Injection Moulding Of Plastics Or The Like (AREA)

Abstract

L'invention concerne un procédé de fabrication d'une garniture d'étanchéité en nid d'abeilles par moulage par injection selon la métallurgie des poudres. Lors du moulage par injection selon la métallurgie des poudres, une poudre métallique et/ou une poudre céramique est d'abord mélangée à au moins un liant pour former une masse homogène. Ensuite, un corps moulé présentant des alvéoles en nid d'abeilles et destiné à former la garniture d'étanchéité en nid d'abeilles est fabriqué à partir de la masse homogène par moulage par injection, ce corps moulé étant ensuite soumis à un processus de déliantage puis comprimé par frittage en une garniture d'étanchéité en nid d'abeilles aux propriétés géométriques souhaitées. Selon la présente invention, au moins quelques-unes des alvéoles du corps moulé sont au moins partiellement remplies d'au moins un corps creux avant le frittage, ledit corps moulé étant ensuite fritté avec les corps creux introduits dans les alvéoles.
EP07722126A 2006-04-06 2007-03-29 Procédé de fabrication d'une garniture d'étanchéité en nid d'abeilles Withdrawn EP2001621A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006016147A DE102006016147A1 (de) 2006-04-06 2006-04-06 Verfahren zum Herstellen einer Wabendichtung
PCT/DE2007/000568 WO2007112727A2 (fr) 2006-04-06 2007-03-29 Procédé de fabrication d'une garniture d'étanchéité en nid d'abeilles

Publications (1)

Publication Number Publication Date
EP2001621A2 true EP2001621A2 (fr) 2008-12-17

Family

ID=38513337

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07722126A Withdrawn EP2001621A2 (fr) 2006-04-06 2007-03-29 Procédé de fabrication d'une garniture d'étanchéité en nid d'abeilles

Country Status (5)

Country Link
US (1) US20090096138A1 (fr)
EP (1) EP2001621A2 (fr)
CA (1) CA2647473A1 (fr)
DE (1) DE102006016147A1 (fr)
WO (1) WO2007112727A2 (fr)

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DE102004029789A1 (de) * 2004-06-19 2006-01-05 Mtu Aero Engines Gmbh Verfahren zum Fertigen von Bauteilen einer Gasturbine sowie Bauteil einer Gasturbine
US7543383B2 (en) * 2007-07-24 2009-06-09 Pratt & Whitney Canada Corp. Method for manufacturing of fuel nozzle floating collar
DE102009016803A1 (de) * 2009-04-09 2010-10-14 Rolls-Royce Deutschland Ltd & Co Kg Labyrinth-Anstreifdichtung für eine Strömungsmaschine
RU2483838C2 (ru) * 2011-04-07 2013-06-10 Общество с ограниченной ответственностью "Научно-производственное предприятие Вакууммаш" Композиционный элемент прирабатываемого уплотнения турбины
RU2483839C2 (ru) * 2011-04-07 2013-06-10 Общество с ограниченной ответственностью "Научно-производственное предприятие Вакууммаш" Армированный элемент прирабатываемого уплотнения турбины
CN102179662A (zh) * 2011-04-27 2011-09-14 沈阳北碳密封有限公司 蜂窝式汽封菱形状正六边形蜂窝加工方法
US10487677B2 (en) * 2015-11-10 2019-11-26 General Electric Company Turbine component having a seal slot and additive manufacturing process for making same
DE102018201295A1 (de) 2018-01-29 2019-08-01 MTU Aero Engines AG Modul für eine strömungsmaschine
US11187100B2 (en) * 2018-12-03 2021-11-30 Raytheon Technologies Corporation CMC honeycomb base for abradable coating on CMC BOAS
CN111138174A (zh) * 2019-12-26 2020-05-12 中国人民解放军军事科学院国防工程研究院工程防护研究所 一种用于人防工程的矾土基泡沫陶瓷球壳的制备方法

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DE10259963B4 (de) * 2002-12-20 2010-04-01 Mtu Aero Engines Gmbh Wabendichtung
DE102004029789A1 (de) * 2004-06-19 2006-01-05 Mtu Aero Engines Gmbh Verfahren zum Fertigen von Bauteilen einer Gasturbine sowie Bauteil einer Gasturbine

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Also Published As

Publication number Publication date
DE102006016147A1 (de) 2007-10-11
WO2007112727A3 (fr) 2007-12-21
CA2647473A1 (fr) 2007-10-11
WO2007112727A2 (fr) 2007-10-11
US20090096138A1 (en) 2009-04-16

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