EP0181255B1 - Verfahren zur Herstellung eines in einen metallischen Träger integrierten keramischen Turbinenringes - Google Patents

Verfahren zur Herstellung eines in einen metallischen Träger integrierten keramischen Turbinenringes Download PDF

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Publication number
EP0181255B1
EP0181255B1 EP85402051A EP85402051A EP0181255B1 EP 0181255 B1 EP0181255 B1 EP 0181255B1 EP 85402051 A EP85402051 A EP 85402051A EP 85402051 A EP85402051 A EP 85402051A EP 0181255 B1 EP0181255 B1 EP 0181255B1
Authority
EP
European Patent Office
Prior art keywords
ceramic element
manufacturing
turbine ring
ceramic
ring 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
Application number
EP85402051A
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English (en)
French (fr)
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EP0181255A1 (de
Inventor
Alain Marie Lardellier
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0181255A1 publication Critical patent/EP0181255A1/de
Application granted granted Critical
Publication of EP0181255B1 publication Critical patent/EP0181255B1/de
Expired legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D25/00—Special casting characterised by the nature of the product
    • 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
    • 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
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • the invention relates to a manufacturing method applicable in particular to turbine rings composed of a ceramic element integrated into an annular metal support.
  • FR-A-2 371 575 thus describes a turbine ring in which a ceramic ring is formed by the juxtaposition of segments.
  • This type of solution requires a relatively complicated and costly method of manufacture and assembly. Furthermore, the inevitable discontinuities, at the level of the coupled edges of the segments, are detrimental to good gas flow.
  • An improvement described by FR-A-2 540 938 provides for elastic fixing of the ceramic segments to a ring by a screw whose head transmits to the segment an axial force which applies it against the ring.
  • FR-A-2 559 634 plans to use a one-piece ceramic ring, which makes it possible to avoid some of the drawbacks mentioned above.
  • the mounting method proposed in this case by means of an annular support made of wound ceramic material, allows a compression prestressing of the ceramic ring but is not however entirely satisfactory in all applications.
  • a ceramic turbine ring makes it possible to avoid the drawbacks noted above and also avoids the use of an additional ring made of wound ceramic material, which makes this solution more complex and also requires the use of connecting means between the ceramic ring and its annular support, such as screws and inserts.
  • the method according to the invention aims to produce a ceramic turbine ring integrated into an annular metal support.
  • the first stage of the process consists of a molding operation in the form of a ceramic element such as 1 visible in FIGS. 1 and 2 representing a later stage of the process.
  • This molding operation only uses methods known commonly used to obtain molded ceramic elements.
  • This ceramic element 1 can constitute a continuous monobloc ring, as shown in FIGS. 1 and 2 and it has pins 2 and 3 on its external diameter and on its internal diameter obtained during the molding operation.
  • the ceramic elements obtained by molding can also be in the form of separate segments or blocks, capable of being assembled to form a ring. Such segments 1a are represented in FIG. 4.
  • a ceramic element can be of the type represented in FIGS. 5 and 6 such as 1b and include on the external diameter of the anchors such as 4 and possibly also on the sides of the ceramic element of the anchors such as 5.
  • These anchors 4 or 5 may or may not be annular and have any shape compatible with their mode of production by molding. These anchoring details can also be applied to the continuous ring of the type shown in FIGS. 1 and 2.
  • This ceramic element 1 thus obtained and defined, in a ring or in segments, is then placed between an internal part 6 and an external part 7 of a tool 8 between which is formed an annular cavity 9, this tool 8 'constituting a casting mold.
  • the pins 2 and 3 mentioned above are used for positioning and holding in place the ceramic element 1 in the annular cavity 9.
  • a centrifugal casting operation is then carried out while respecting the precautions specific to this known casting method.
  • the molten metal is introduced into the tool 8 which, during this time, is rotated about its axis.
  • the annular cavity 9 is filled with molten metal and the tool 8 is kept in rotation until the metal solidifies completely.
  • This finished part 10 shown in Figures 3 and 4 thus consists of a ceramic element 1 held inside a metal support 11 to which this ceramic element 1 adheres perfectly.
  • the metal support 11 includes one, or more, flange (s) such as 12 used for assembling the part in the turbine (see FIG. 3).
  • the metallic material exerts a compression of the ceramic element 1. It a compression prestress of the ceramic results which may be weak, or even cancel out in operation, when the ring is used after mounting on a turbine, but in no case does it appear any tensile force of the support metal on the ceramic, which would be seriously detrimental to good service performance of the ceramic element.
  • a type of ceramic which is best suited to the conditions of use envisaged can be chosen for the manufacture of the ceramic element 1.
  • a homogeneous or composite ceramic can be used.
  • the pins 2 or 3 intended to hold the ceramic element 1 between the two parts 6 and 7 of the tool 8 before and during the metal casting operation can be replaced by attached spacers.
  • the annular housing of the ceramic element 1 in the metal support 11 can have any shape of section, rectangular or trapezoidal or other.
  • the annular part 10 obtained before mounting on a turbine can also be segmented by sawing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Ceramic Products (AREA)
  • Devices For Post-Treatments, Processing, Supply, Discharge, And Other Processes (AREA)

Claims (12)

1. Verfahren zur Herstellung eines in einem ringförmigen metallischen Träger integrierten keramischen Turbinenrings, gekennzeichnet durch folgende Verfahrensschritte :
a) Formgießen eines Keramikelements (1 ; 1a ; 1 b),
b) Plazieren des in dem Verfahrensschritt a) erhaltenen Keramikelements (1 ; 1a ; 1b) in dem ringförmigen Hohlraum (9) einer eine Gußform bildenden Gerätschaft (8),
c) Schleudergießen eines metallischen Werkstoffs in den Hohlraum (9) der genannten Gußform (8), die bis zum Beendigen der Verfestigung in Rotation gehalten wird,
d) Entformen des in dem Verfahrensschritt c) erhaltenen Teils (10) durch Demontieren der Gußform (8),
e) Materialabtragende Bearbeitung des in dem Verfahrensschritt d) erhaltenen Teils (10) in der Weise, daß das erhaltene Teil (10) als Turbinenring verwendbar ist, der aus einem in einen ringförmigen metallischen Träger (11) eingelassenen ringförmigen Keramikelement (1 ; 1a; 1b) besteht.
2. Verfahren zur Herstellung eines Turbinenrings nach Anspruch 1, dadurch gekennzeichnet, daß das in dem Verfahrensschritt a) erhaltene Keramikelement (1 ; 1a ; 1 b) aus einer homogenen Keramik besteht.
3. Verfahren zur Herstellung eines Turbinenrings nach Anspruch 1, dadurch gekennzeichnet, daß das in dem Verfahrensschritt a) erhaltene Keramikelement (1 ; 1a ; 1b) aus einer Verbundkeramik besteht.
4. Verfahren zur Herstellung eines Turbinenrings nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß das Keramikelement (1 ; 1a ; 1b) in den Verfahrensschritten b) und c) mit Hilfe von keramischen Stegen in der Gerätschaft (8) gehalten wird.
5. Verfahren zur Herstellung eines Turbinenrings nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß das in dem Verfahrensschritt a) erhaltene Keramikelement (1 : 1a : 1b) Spitzen (2, 3) aufweist, die dazu dienen, das Keramikelement (1 ; 1a ; 1b) in den Verfahrensschritten b) und c) in der Gerätschaft (8) zu halten.
6. Verfahren zur Herstellung eines Turbinenrings nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß das Keramikelement ein aus einem Block bestehender Ring ist.
7. Verfahren zur Herstellung eines Turbinenrings nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß das Keramikelement (1a) aus Segmenten besteht, die in dem Verfahrensschritt b) ringförmig angeordnet werden.
8. Verfahren zur Herstellung eines Turbinenrings nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das in dem Verfahrensschritt a) erhaltene Keramikelement (1b) weibliche Verankerungselemente (4 ; 5) aufweist, die sich in dem Verfahrensschritt c) mit metallischem Werkstoff füllen, derart daß sie von da an ein Haften des Keramikelements in dem ringförmigen metallischen Träger bewirken.
9. Verfahren zur Herstellung eines Turbinenrings nach Anspruch 8, dadurch gekennzeichnet, daß die genannten Verankerungselemente (4 ; 5) auf dem Außendurchmesser und auf den Flanken des Keramikelements ausgebildet sind.
10. Verfahren zur Herstellung eines Turbinenrings nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der Verfahrensschritt c) ein Gießen im Vakuum ist.
11. Verfahren zur Herstellung eines Turbinenrings nach einem der Ansprüche 1 bis 9. dadurch gekennzeichnet, daß der Verfahrensschritt c) ein Gießsen in einer Schutzatmosphäre ist.
12. Verfahren zur Herstellung eines Turbinenrings nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die materialabtragende Bearbeitung in dem Verfahrensschritt e) ein Segmentieren durch Zersägen des ringförmigen Teils (10) umfaßt.
EP85402051A 1984-10-30 1985-10-23 Verfahren zur Herstellung eines in einen metallischen Träger integrierten keramischen Turbinenringes Expired EP0181255B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8416535 1984-10-30
FR8416535A FR2572394B1 (fr) 1984-10-30 1984-10-30 Procede de fabrication d'un anneau de turbine en ceramique integre a un support metallique annulaire

Publications (2)

Publication Number Publication Date
EP0181255A1 EP0181255A1 (de) 1986-05-14
EP0181255B1 true EP0181255B1 (de) 1987-12-23

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP85402051A Expired EP0181255B1 (de) 1984-10-30 1985-10-23 Verfahren zur Herstellung eines in einen metallischen Träger integrierten keramischen Turbinenringes

Country Status (5)

Country Link
US (1) US4646810A (de)
EP (1) EP0181255B1 (de)
JP (1) JPS61119370A (de)
DE (1) DE3561231D1 (de)
FR (1) FR2572394B1 (de)

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JPH0791352B2 (ja) * 1987-11-20 1995-10-04 住友デュレズ株式会社 シェルモールド用ノボラック型フェノール樹脂の製造方法
FR2646473B1 (fr) * 1989-04-26 1991-07-05 Snecma Moteur a soufflantes contrarotatives tractrices
US5062767A (en) * 1990-04-27 1991-11-05 The United States Of America As Represented By The Secretary Of The Air Force Segmented composite inner shrouds
US5413647A (en) * 1992-03-26 1995-05-09 General Electric Company Method for forming a thin-walled combustion liner for use in a gas turbine engine
US5447411A (en) * 1993-06-10 1995-09-05 Martin Marietta Corporation Light weight fan blade containment system
US6000906A (en) * 1997-09-12 1999-12-14 Alliedsignal Inc. Ceramic airfoil
US6758653B2 (en) 2002-09-09 2004-07-06 Siemens Westinghouse Power Corporation Ceramic matrix composite component for a gas turbine engine
WO2007064605A2 (en) 2005-11-30 2007-06-07 Dresser-Rand Company End closure device for a turbomachine casing
EP1865258A1 (de) * 2006-06-06 2007-12-12 Siemens Aktiengesellschaft Gepanzerte Maschinenkomponente und Gasturbine
US8528339B2 (en) 2007-04-05 2013-09-10 Siemens Energy, Inc. Stacked laminate gas turbine component
CA2896500A1 (en) * 2013-01-29 2014-08-07 Rolls-Royce Corporation Turbine shroud
EP2769969B1 (de) * 2013-02-25 2018-10-17 Ansaldo Energia IP UK Limited Verfahren zur Herstellung einer Metall-Keramik-Verbundstruktur sowie Metall-Keramik-Verbundstruktur
US10094233B2 (en) 2013-03-13 2018-10-09 Rolls-Royce Corporation Turbine shroud
DE102013213834A1 (de) * 2013-07-15 2015-02-19 MTU Aero Engines AG Verfahren zum Herstellen eines Isolationselements und Isolationselement für ein Gehäuse eines Flugtriebwerks
US10190434B2 (en) 2014-10-29 2019-01-29 Rolls-Royce North American Technologies Inc. Turbine shroud with locating inserts
CA2915246A1 (en) 2014-12-23 2016-06-23 Rolls-Royce Corporation Turbine shroud
CA2915370A1 (en) 2014-12-23 2016-06-23 Rolls-Royce Corporation Full hoop blade track with axially keyed features
EP3045674B1 (de) 2015-01-15 2018-11-21 Rolls-Royce Corporation Turbinenummantelung mit rohrförmigen laufradpositionierungseinsätzen
CA2925588A1 (en) 2015-04-29 2016-10-29 Rolls-Royce Corporation Brazed blade track for a gas turbine engine
CA2924855A1 (en) 2015-04-29 2016-10-29 Rolls-Royce Corporation Keystoned blade track
US10125788B2 (en) 2016-01-08 2018-11-13 General Electric Company Ceramic tile fan blade containment
US10240476B2 (en) 2016-01-19 2019-03-26 Rolls-Royce North American Technologies Inc. Full hoop blade track with interstage cooling air
US10415415B2 (en) 2016-07-22 2019-09-17 Rolls-Royce North American Technologies Inc. Turbine shroud with forward case and full hoop blade track
US10287906B2 (en) 2016-05-24 2019-05-14 Rolls-Royce North American Technologies Inc. Turbine shroud with full hoop ceramic matrix composite blade track and seal system
CN110723966B (zh) * 2019-11-13 2022-04-01 中国航发南方工业有限公司 扇形片状陶瓷型芯的制备方法
CN112723899A (zh) * 2020-12-31 2021-04-30 淮安市浩远机械制造有限公司 一种氧化铝陶瓷钎焊合金钢复合耐磨板及其制备工艺

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Also Published As

Publication number Publication date
US4646810A (en) 1987-03-03
JPS61119370A (ja) 1986-06-06
JPH0247309B2 (de) 1990-10-19
FR2572394B1 (fr) 1986-12-19
DE3561231D1 (en) 1988-02-04
FR2572394A1 (fr) 1986-05-02
EP0181255A1 (de) 1986-05-14

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