EP0181255B1 - Procédé de fabrication d'un anneau de turbine en céramique intégré à un support métallique annulaire - Google Patents

Procédé de fabrication d'un anneau de turbine en céramique intégré à un support métallique annulaire Download PDF

Info

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
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0181255A1 (fr
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/fr
Application granted granted Critical
Publication of EP0181255B1 publication Critical patent/EP0181255B1/fr
Expired legal-status Critical Current

Links

Images

Classifications

    • 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)
EP85402051A 1984-10-30 1985-10-23 Procédé de fabrication d'un anneau de turbine en céramique intégré à un support métallique annulaire Expired EP0181255B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
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
FR8416535 1984-10-30

Publications (2)

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

Family

ID=9309108

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85402051A Expired EP0181255B1 (fr) 1984-10-30 1985-10-23 Procédé de fabrication d'un anneau de turbine en céramique intégré à un support métallique annulaire

Country Status (5)

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

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4914794A (en) * 1986-08-07 1990-04-10 Allied-Signal Inc. Method of making an abradable strain-tolerant ceramic coated turbine shroud
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
EP1960632B1 (en) 2005-11-30 2019-08-21 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 (en) * 2013-02-25 2018-10-17 Ansaldo Energia IP UK Limited Method for manufacturing a metal-ceramic composite structure and metal-ceramic composite structure
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 (en) 2015-01-15 2018-11-21 Rolls-Royce Corporation Turbine shroud with tubular runner-locating inserts
CA2924855A1 (en) 2015-04-29 2016-10-29 Rolls-Royce Corporation Keystoned blade track
CA2925588A1 (en) 2015-04-29 2016-10-29 Rolls-Royce Corporation Brazed blade track for a gas turbine engine
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

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3401026A (en) * 1966-01-19 1968-09-10 Gen Motors Corp Method of forming a bimetallic article
US3511306A (en) * 1969-03-17 1970-05-12 Certain Teed St Gobain Method and apparatus for centrifugally casting perforated rings
BE792224A (fr) * 1971-12-01 1973-03-30 Penny Robert N Element composite long ayant un coefficient de dilatation lineaire effectif predetermine
US4112574A (en) * 1976-11-02 1978-09-12 International Harvester Company Torsielastic thrust bushing for track chains
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
US4135851A (en) * 1977-05-27 1979-01-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
US4377196A (en) * 1980-07-14 1983-03-22 Abex Corporation Method of centrifugally casting a metal tube
US4426193A (en) * 1981-01-22 1984-01-17 The United States Of America As Represented By The Secretary Of The Air Force Impact composite blade
FR2540939A1 (fr) * 1983-02-10 1984-08-17 Snecma Anneau d'etancheite pour un rotor de turbine d'une turbomachine et installation de turbomachine munie de tels anneaux
FR2540938B1 (fr) * 1983-02-10 1987-06-05 Snecma Anneau de turbine d'une turbomachine

Also Published As

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

Similar Documents

Publication Publication Date Title
EP0181255B1 (fr) Procédé de fabrication d'un anneau de turbine en céramique intégré à un support métallique annulaire
EP1637253B1 (fr) Procédé de fabrication d'une aube de turbomachine, assemblage de noyaux pour la mise en oeuvre du procédé
FR2604116A1 (fr) Procede pour fabriquer une roue a aubes pour une pompe a agent refrigerant d'un vehicule automobile
FR2567062A1 (fr) Element annulaire a aubes ayant un anneau de renforcement integrant et son dispositif de fabrication
EP1880789A1 (fr) Procédé de fabrication d'un disque aubage monobloc et moule pour la mise en oeuvre du procédé
US10441997B2 (en) Casting mold, insert for a casting mold, a cast part and a casting method therefor
EP3164237B1 (fr) Procédé de fabrication d'une aube bi-composant pour moteur à turbine à gaz et aube obtenue par un tel procédé
EP3827505A1 (fr) Dispositif de guidage de fils pour rotor de machine électrique synchrone de type à rotor bobiné
EP0618996B1 (fr) Procede de fabrication d'une roue de turbine a aubes inserees et roue obtenue par le procede
FR2950825A1 (fr) Procede ameliore de fabrication d'un ensemble annulaire aubage de turbomachine a la cire perdue, moule metallique et modele en cire pour la mise en oeuvre d'un tel procede
CA2589077C (fr) Procede de fabrication d'un disque de rotor de turbomachine
JP2003254076A (ja) タービンホイールランナの製作方法
FR2949091A1 (fr) Procede de realisation d'un disque aubage monobloc creux
FR2642688A1 (fr) Procede pour realiser la liaison entre des disques de rotor en alliage de titane et de nickel de turbomachines, notamment de rotors de compresseur
FR2711755A1 (fr) Roue de turbine et/ou de pompe et procédé de réalisation de celle-ci.
EP2397245B1 (fr) Ensemble de strates, moule, procédés de confection de ce modèle et de fabrication d'une pièce à partir de ce modele
FR2620077A1 (fr) Procede de fabrication de couvercles de protection d'organes pour moteurs de vehicules automobiles, par injections successives de polymere et d'elastomere et couvercle obtenu par ce procede
FR2866838A1 (fr) Piece utilisable en mecanique comportant au moins un surmoulage
FR2664005A1 (fr) Procede de fabrication d'un boitier d'etrier de frein, pour frein a disque, et boitier d'etrier de frein obtenu par ce procede.
EP4076836A1 (fr) Solution de fabrication d'un disque aubage monobloc
FR2504425A1 (fr) Procede de fabrication d'une piece en metal fritte a partir d'un melange pateux moule, et moule pour la mise en oeuvre du procede
BE1010995A3 (fr) Assemblage a engagement positif de moules ceramiques.
FR3108539A1 (fr) Procede de solidification dirigee pour alliages metalliques et modele en materiau eliminable pour le procede
FR3139741A1 (fr) Grappe de modeles realises en cire et moule pour la fabrication par moulage a cire perdue d’une pluralite d’elements de turbomachine
EP3969202A1 (fr) Moule pour la fabrication d'une piece par coulee de metal et croissance epitaxiale et procede de fabrication associe

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19851111

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB IT SE

17Q First examination report despatched

Effective date: 19870507

ITF It: translation for a ep patent filed

Owner name: BARZANO' E ZANARDO MILANO S.P.A.

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT SE

REF Corresponds to:

Ref document number: 3561231

Country of ref document: DE

Date of ref document: 19880204

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: FR

Ref legal event code: CL

ITTA It: last paid annual fee
EAL Se: european patent in force in sweden

Ref document number: 85402051.8

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20030922

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20030924

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20031022

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20031219

Year of fee payment: 19

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20041023

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20041024

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050503

EUG Se: european patent has lapsed
GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20041023

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050630

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST