EP0967363B1 - Joint de type nid d'abeille spécialement pour une turbine à gaz - Google Patents

Joint de type nid d'abeille spécialement pour une turbine à gaz Download PDF

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Publication number
EP0967363B1
EP0967363B1 EP99110083A EP99110083A EP0967363B1 EP 0967363 B1 EP0967363 B1 EP 0967363B1 EP 99110083 A EP99110083 A EP 99110083A EP 99110083 A EP99110083 A EP 99110083A EP 0967363 B1 EP0967363 B1 EP 0967363B1
Authority
EP
European Patent Office
Prior art keywords
honeycomb
section
honeycomb structure
turbine
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.)
Expired - Lifetime
Application number
EP99110083A
Other languages
German (de)
English (en)
Other versions
EP0967363A3 (fr
EP0967363A2 (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 EP0967363A2 publication Critical patent/EP0967363A2/fr
Publication of EP0967363A3 publication Critical patent/EP0967363A3/fr
Application granted granted Critical
Publication of EP0967363B1 publication Critical patent/EP0967363B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D11/127—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
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S277/00—Seal for a joint or juncture
    • Y10S277/913—Seal for fluid pressure below atmospheric, e.g. vacuum
    • 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
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49297—Seal or packing making
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24149—Honeycomb-like

Definitions

  • the invention relates to a honeycomb structure seal between a rotating Element and a stator element of a turbine, in particular for one Gas turbine, with one facing the tips of the turbine blades Scraping section as well as with one facing the other element of the turbine Baseplate.
  • the term "honeycomb structure" is to be understood generally, i.e. it does not necessarily have to be the honeycomb structure familiar to the person skilled in the art act. Rather, this includes any arrangement of to understand adjacent cavities of any geometry.
  • honeycomb structure seals also called “honeycomb seals”.
  • the honeycomb structure is supported by a base plate while the web walls forming the honeycomb structure with their free end sections are facing the tips of the rotor blades.
  • the one from the Web walls with limited honeycomb cells can at least partially be included be filled with a suitable insulation material, as described in the above scripture is described.
  • the object of the present invention is to provide a remedial measure for the problems described.
  • the solution to this problem is characterized by a multi-layer structure of the honeycomb structure seal in such a way that an air-evacuated honeycomb structure section, which is thus partially insulated by vacuum, connects to the base plate and is covered by an intermediate plate on its side facing away from the honeycomb structure section the brushing section is arranged.
  • Advantageous training and further education are included in the subclaims. It should be pointed out again that the so-called honeycomb structure section is to be understood as an arrangement of several cavities of essentially any shape next to one another.
  • Reference number 1 denotes a base plate, on the surface thereof a honeycomb structure which is customary in honeycomb seals is. This honeycomb structure adjacent to the base plate 1 is referred to below as Honeycomb structure section 2 of the honeycomb structure seal according to the invention designated.
  • An intermediate plate 3 adjoins the honeycomb structure section 2 on the side opposite the base plate 1, ie the honeycomb structure section 2 is covered by the intermediate plate 3.
  • the attached figure is an exploded view, ie in reality the honeycomb structure section 2 is embedded directly between the base plate 1 on the one hand and the intermediate plate 3 on the other hand.
  • a so-called rubbing section 4 is arranged on the intermediate plate 3. This brushing section 4 also lies directly on the intermediate plate 3.
  • honeycomb structure seal shown and described so far draws is thus characterized by a multi-layer structure consisting of the base plate 1, the honeycomb structure section 2, the intermediate plate 3 and the brushing section 4.
  • the base plate 1 In the installed state of this honeycomb structure seal in one Turbine, in particular an aircraft gas turbine, is the base plate 1 with their free (here lower) surface on the inner wall of the not shown Turbine housing, while the (upper in the figure) free surface of the brushing section 4 (also not shown) Blade tips facing the turbine rotor blades.
  • the brushing section 4 is necessary in view Sealing effect, i.e. on the sealing of the gap between those not shown Blade tips and the honeycomb structure seal formed.
  • this brushing section 4 on which the blade tips for achieving can or should actually rub against an optimal sealing effect, can therefore be a brush seal, a plasma spray coating, a metal felt or a "Metco" layer known to the person skilled in the art, or other suitable sealing structures.
  • the shown here The exemplary embodiment is this brushing section 4 itself again in shape a (usual per se) honeycomb seal, i.e. it exists as usual from a variety of honeycomb-shaped, for example, or preferably arranged web walls 5, each of which form so-called honeycomb cells 6.
  • the sealing function of the honeycomb structure seal according to the invention is taken from section 2 of the honeycomb structure.
  • the latter is air evacuated, i.e. in the partial areas of the individual honeycomb cells 6 of the honeycomb structure section 2 there is thermal insulation due to vacuum. So that the vacuum present in the honeycomb cells 6 at least essentially is preserved, it is of course necessary that the honeycomb cells 6 (in the figure display up and down) completed are what through the base plate 1 on the one hand and through the intermediate plate 3 on the other hand is guaranteed.
  • honeycomb structure section 2 and the base plate 1 and the intermediate plate 3 formed section the honeycomb structure seal by high temperature soldering under vacuum conditions.
  • the intermediate plate 3 is soldered.
  • the brushing section 4 is connected to the intermediate plate 3 become.
  • honeycomb structure seal proposed here thus consists of two, by an intermediate plate 3 separated honeycomb structures, namely the honeycomb structure section 2 and the brushing section 4.
  • honeycomb structures can be commercially available and preferably consist of thin, metallic high-temperature alloys.
  • the (here lower) honeycomb structure section 3 takes over the function of thermal insulation; accordingly, he can constructively Varying the structure size and height of the required insulation characteristics be adjusted. Because the desired thermal Isolation effect by the prevailing in the honeycomb cells 6 (at least essentially) vacuum is achieved, these honeycomb cells 6 should be preferred have the largest possible base or cross-sectional area.
  • the upper sealing honeycomb structure i.e. the Brushing section 4 in its / its execution to the requirements of Sealing effect with respect to the turbine working gas flowing past it customized.
  • the achievable sealing effect is better, the smaller the basic or cross-sectional areas of the honeycomb cells 6 of this honeycomb structure. Accordingly, as can be seen, it is provided that the honeycomb cells 6 of the Honeycomb formed trained streak section 4 a significantly smaller Have partial area as the honeycomb cells 6 of the honeycomb structure section Second
  • the vacuum-insulated Honeycomb structure section 2 alternatively as an insulating substructure for one other than the brushing section 4 shown, i.e.
  • other sealing systems can also be used, such as e.g. a brush seal, METCO layers, plasma spray layers, Metal felts or the like, each based on the vacuum insulation structure described can be applied.
  • a brush seal e.g. a brush seal, METCO layers, plasma spray layers, Metal felts or the like

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (4)

  1. Joint à structure alvéolaire compris entre un élément rotatif et un élément de stator d'une turbine, notamment d'une turbine à gaz, comportant un segment de raclage (4) tourné vers les pointes des aubes de la turbine ainsi qu'une plaque de base (1) tournée vers l'autre élément de la turbine,
    caractérisé par
    une structure en plusieurs couches avec un segment de structure alvéolaire (2) adjacent à la plaque de base (1), vide d'air et ainsi isolé par le vide en surface partielle, ce segment étant couvert par une plaque intermédiaire (3), recevant le segment de raclage (4) sur la face opposée de la structure alvéolaire (2).
  2. Joint à structure alvéolaire selon la revendication 1,
    caractérisé en ce que
    la plaque intermédiaire (3) est soudée au segment de structure alvéolaire (2), ce procédé de fabrication étant fait sous vide.
  3. Joint à structure alvéolaire selon la revendication 1 ou 2,
    caractérisé en ce que
    le segment de raclage (4) est également constitué par un joint alvéolaire.
  4. Joint à structure alvéolaire selon l'une des revendications précédentes,
    caractérisé en ce que
    les alvéoles (6) du segment de raclage (4) en forme de joint alvéolaire ont une section partielle significativement plus petite que les alvéoles (6) du segment de structure alvéolaire (2).
EP99110083A 1998-06-24 1999-05-22 Joint de type nid d'abeille spécialement pour une turbine à gaz Expired - Lifetime EP0967363B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19828065 1998-06-24
DE19828065A DE19828065A1 (de) 1998-06-24 1998-06-24 Wabenstruktur-Dichtung insbesondere für eine Gasturbine

Publications (3)

Publication Number Publication Date
EP0967363A2 EP0967363A2 (fr) 1999-12-29
EP0967363A3 EP0967363A3 (fr) 2000-11-22
EP0967363B1 true EP0967363B1 (fr) 2003-05-02

Family

ID=7871828

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99110083A Expired - Lifetime EP0967363B1 (fr) 1998-06-24 1999-05-22 Joint de type nid d'abeille spécialement pour une turbine à gaz

Country Status (3)

Country Link
US (1) US6251494B1 (fr)
EP (1) EP0967363B1 (fr)
DE (2) DE19828065A1 (fr)

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DE102004034312A1 (de) * 2004-07-15 2006-02-02 Mtu Aero Engines Gmbh Dichtungsanordnung und Verfahren zur Herstellung eines Dichtkörpers für eine Dichtungsanordnung
US20070137039A1 (en) * 2005-12-20 2007-06-21 General Electric Company Methods and apparatus for coupling honeycomb seals to gas turbine engine components
US7932633B2 (en) 2008-10-22 2011-04-26 General Electric Company Apparatus for transferring energy using power electronics and machine inductance and method of manufacturing same
US8080973B2 (en) 2008-10-22 2011-12-20 General Electric Company Apparatus for energy transfer using converter and method of manufacturing same
US9290097B2 (en) 2010-11-05 2016-03-22 Robert Louis Steigerwald Apparatus for transferring energy using onboard power electronics with high-frequency transformer isolation and method of manufacturing same
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CN102979906A (zh) * 2012-08-29 2013-03-20 哈尔滨汽轮机厂有限责任公司 用于燃气轮机的蜂窝密封装置的加工方法
JP6184173B2 (ja) 2013-05-29 2017-08-23 三菱日立パワーシステムズ株式会社 ガスタービン
US20160215646A1 (en) * 2013-09-06 2016-07-28 General Electric Company Gas turbine laminate seal assembly comprising first and second honeycomb layer and a perforated intermediate seal plate in-between
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
DE102015216208A1 (de) * 2015-08-25 2017-03-02 Rolls-Royce Deutschland Ltd & Co Kg Dichtelement für eine Turbomaschine, Turbomaschine mit einem Dichtelement und Verfahren zur Herstellung eines Dichtelementes
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US10774670B2 (en) * 2017-06-07 2020-09-15 General Electric Company Filled abradable seal component and associated methods thereof
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US11674396B2 (en) 2021-07-30 2023-06-13 General Electric Company Cooling air delivery assembly
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Also Published As

Publication number Publication date
DE59905282D1 (de) 2003-06-05
DE19828065A1 (de) 1999-12-30
EP0967363A3 (fr) 2000-11-22
US6251494B1 (en) 2001-06-26
EP0967363A2 (fr) 1999-12-29

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