EP2241724A2 - Joint labyrinthe abradable pour une turbomachine - Google Patents

Joint labyrinthe abradable pour une turbomachine Download PDF

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Publication number
EP2241724A2
EP2241724A2 EP10002769A EP10002769A EP2241724A2 EP 2241724 A2 EP2241724 A2 EP 2241724A2 EP 10002769 A EP10002769 A EP 10002769A EP 10002769 A EP10002769 A EP 10002769A EP 2241724 A2 EP2241724 A2 EP 2241724A2
Authority
EP
European Patent Office
Prior art keywords
labyrinth
rubbing
hollow body
sealing
seal 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Withdrawn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
EP10002769A
Other languages
German (de)
English (en)
Other versions
EP2241724A3 (fr
Inventor
Karl Schreiber
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2241724A2 publication Critical patent/EP2241724A2/fr
Publication of EP2241724A3 publication Critical patent/EP2241724A3/fr
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • B22F3/10—Sintering only
    • B22F3/11—Making porous workpieces or articles
    • B22F3/1103—Making porous workpieces or articles with particular physical characteristics
    • B22F3/1112—Making porous workpieces or articles with particular physical characteristics comprising hollow spheres or hollow fibres
    • 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
    • B22F3/10—Sintering only
    • B22F3/11—Making porous workpieces or articles
    • B22F3/1121—Making porous workpieces or articles by using decomposable, meltable or sublimatable fillers
    • 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
    • B22F3/12—Both compacting and sintering
    • B22F3/14—Both compacting and sintering simultaneously
    • 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
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades

Definitions

  • the invention relates to a labyrinth-abradable seal for a turbomachine for sealing a sealing gap formed between a stationary carrier provided with a Abst slaughter of hollow material formed by porous body and a directed onto the Abst slaughter sealing webs rotating component, in particular for hot gas sealing in the turbine of a gas turbine engine.
  • the Anstreifdichtonne should not only prevent flow around the relevant stage of the turbomachine, but also the housing structure, for example, the hot gas in a turbine stage leading wall sections, thermally isolate or control the passing into the wall sections heat flow so that the thermal expansion of the stationary Components or the housing expansion according to the thermal expansion of the rotating components, that is, the rotor disks and blades, takes place and so depending is ensured by the operating conditions or hot gas temperatures as small a gap as possible.
  • the EP 1013890 B1 describes a labyrinth rubbing seal whose abradable layer consists entirely of a high temperature, foamed, metallic, corrosion-resistant alloy, that is, a closed-cell metal foam in which thin walls enclose a plurality of cavities between them.
  • a closed-cell metal foam in which thin walls enclose a plurality of cavities between them.
  • the foam structure used as the run-in layer has a high heat-insulating effect. Due to the irregular foam structure, however, material accumulations and consequent strong warming as well as break-outs from the brittle metal foam structure may also occur here.
  • the invention has for its object to provide a labyrinth-squeal with adapted to the particular application heat insulation and reliable sealing effect and long life.
  • the object is achieved with a trained according to the features of claim 1 labyrinth rubbing seal.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • the essence of the invention is that in shape and size matching hollow body in the X, Y and Z directions are arranged exactly linear side by side and one above the other and are connected flat and form an orderly open to closed cell structure, the hollow bodies are arranged and aligned so that the tips the sealing ridges meet approximately centrally on the hollow bodies.
  • the hollow bodies are arranged in such a way that the tips of the sealing webs essentially rub the hollow bodies centrally, accumulation of material does not occur and thus also does not lead to excessive heating leading to crack formation on the sealing webs. This ensures a reliable sealing effect, safe operation and a longer service life of the turbomachine.
  • the degree of open porosity may vary and, with the maximum thermal insulation required, may also be zero.
  • FIG. 1 partially reproduced low-pressure turbine of a gas turbine engine are three with the low-pressure turbine shaft via a rotor arm 1 and interconnected via connecting webs 2 rotor disks 3 with attached thereto turbine blades 4 (rotating component) shown. Between the turbine blades 4 5 fixed vanes 6 (stationary component) are arranged on the turbine housing. At the tips of the turbine blades 4 mounted shrouds 7 each form three in the circumferential direction and transverse to the flow direction sealing webs 8. Such sealing webs 8 are also attached to the connecting webs 2 between the rotor disks 3.
  • a squeal 10 On a on the inside of the turbine housing 5 relative to the sealing webs 8 of the shrouds 7 mounted carrier 9 is - for example, by soldering - a squeal 10 attached. Such trained with a squeal layer 10 carrier 9 is also provided on connected to the tips of the vanes 6 shrouds 7.
  • the abradable layer 10 is designed such that, upon contact with the sealing webs 8, the material of the abradable layer 10 is removed, that is, the tips of the sealing webs 8 can penetrate into the abradable layer, and thus a very narrow sealing gap and a high sealing effect and a corresponding high efficiency of the turbomachine can be achieved.
  • the abradable layer 10 consists of a defined, ordered cellular structure made of sintered and pressurized high temperature resistant, consisting of a sintered material, in shape and size substantially identical hollow bodies 11, the linear in the X, Y and Z directions are aligned exactly to each other and here form three superimposed hollow body layers 13.
  • An essential feature The labyrinth rubbing seal consists in that the hollow bodies 11 of the rubbing layer 10 are positioned with respect to the sealing webs 8 so that their tips are directed substantially centrally on the hollow body 11 of the rubbing layer 10.
  • the ordered cell structure for the rubbing layer 10 is produced by sintering polystyrene beads coated with a sinterable metal powder.
  • the green spheres coated with the sintered material in accordance with the desired wall thickness and not yet sintered are introduced into a mold to produce the hollow body structure (rubbing layer 10) and sintered in this mold under the effect of pressure and temperature and simultaneously bonded together by sintering.
  • the hollow spheres formed during sintering are flattened at the contact surfaces with the mold wall or the adjacent hollow spheres and - as Fig. 2 shows - deformed in the present embodiment at the top and bottom more than at the sides flattened (elongated) hollow bodies 11 with mutual surface contact.
  • the elongated shape allows for smaller hollow bodies 11 a preferred central positioning to the tips of the sealing webs 8, so that when accumulating no accumulations of material and associated high temperatures are generated.
  • the ordered cell structure of the squealer layer 10 may be as shown in FIG Fig. 2 shown - open-pore, that is to be formed with pores 12 open to the outside, or closed-cell. Also the size of the open-pored area and the thereby possible hot gas flow or the degree of thermal insulation with respect to the stationary component (turbine housing) can be varied during the production of the hollow body structure.
  • a closed-pore or largely closed-pore formation causes a high heat insulation required in particular in the area of the high-pressure turbine and thus a small gap between the turbine blades and the turbine housing and ultimately low power losses.
  • a certain open porosity of the squeal layer may be provided in order to be able to influence the gap width. If appropriate, cooling air can also be directed through an open-pored structure to reduce the hot gas influence.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
EP10002769.7A 2009-04-09 2010-03-16 Joint labyrinthe abradable pour une turbomachine Withdrawn EP2241724A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009016803A DE102009016803A1 (de) 2009-04-09 2009-04-09 Labyrinth-Anstreifdichtung für eine Strömungsmaschine

Publications (2)

Publication Number Publication Date
EP2241724A2 true EP2241724A2 (fr) 2010-10-20
EP2241724A3 EP2241724A3 (fr) 2014-01-15

Family

ID=42237305

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10002769.7A Withdrawn EP2241724A3 (fr) 2009-04-09 2010-03-16 Joint labyrinthe abradable pour une turbomachine

Country Status (3)

Country Link
US (1) US20100259013A1 (fr)
EP (1) EP2241724A3 (fr)
DE (1) DE102009016803A1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150377123A1 (en) 2007-08-01 2015-12-31 United Technologies Corporation Turbine section of high bypass turbofan
US11346289B2 (en) 2007-08-01 2022-05-31 Raytheon Technologies Corporation Turbine section of high bypass turbofan
US11486311B2 (en) 2007-08-01 2022-11-01 Raytheon Technologies Corporation Turbine section of high bypass turbofan
US11242805B2 (en) 2007-08-01 2022-02-08 Raytheon Technologies Corporation Turbine section of high bypass turbofan
US11149650B2 (en) 2007-08-01 2021-10-19 Raytheon Technologies Corporation Turbine section of high bypass turbofan
US20110120263A1 (en) * 2009-11-23 2011-05-26 Short Keith E Porous metal gland seal
EP2647795B1 (fr) * 2012-04-04 2018-11-07 MTU Aero Engines AG Système d'étanchéité pour turbomachine
EP3085900B1 (fr) * 2015-04-21 2020-08-05 Ansaldo Energia Switzerland AG Lèvre abradable pour une turbine à gaz
CN105134954A (zh) * 2015-09-14 2015-12-09 沈阳航空航天大学 一种提高封严特性与阻尼特性的新型孔型密封结构
CN105156680A (zh) * 2015-09-14 2015-12-16 沈阳航空航天大学 一种提高封严特性与阻尼特性的新型蜂窝密封结构
DE102018107433A1 (de) 2018-03-28 2019-10-02 Rolls-Royce Deutschland Ltd & Co Kg Einlaufbelagstruktur aus einem metallischen Werkstoff, Verfahren zur Herstellung einer Einlaufbelagstruktur und Bauteil mit einer Einlaufbelagstruktur

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1013890B1 (fr) 1998-12-16 2004-02-04 Rolls-Royce Deutschland Ltd & Co KG Joint abradable pour turbomachines

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Publication number Priority date Publication date Assignee Title
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Also Published As

Publication number Publication date
DE102009016803A1 (de) 2010-10-14
EP2241724A3 (fr) 2014-01-15
US20100259013A1 (en) 2010-10-14

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