EP0181255A1 - 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
EP0181255A1
EP0181255A1 EP85402051A EP85402051A EP0181255A1 EP 0181255 A1 EP0181255 A1 EP 0181255A1 EP 85402051 A EP85402051 A EP 85402051A EP 85402051 A EP85402051 A EP 85402051A EP 0181255 A1 EP0181255 A1 EP 0181255A1
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.)
Granted
Application number
EP85402051A
Other languages
English (en)
French (fr)
Other versions
EP0181255B1 (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
SNECMA SAS
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, SNECMA SAS 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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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.
  • F R -A-2 559 634 plans to use a one-piece ceramic ring, which avoids some of the drawbacks mentioned above.
  • the mounting method proposed in this case by means of an annular support of wound ceramic material, allows the compression of the ceramic ring to be prestressed, 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 known methods 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 comprises on its external diameter and on its internal diameter pins 2 and 3 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 shown in FIG. 4.
  • a ceramic element can be of the type shown in FIGS. 5 and 6 such as lb and have anchors such as 4 on the external diameter and possibly also on the sides of the ceramic element anchors such 5.
  • These anchors 4 or 5 may or may not be annular and have any shape compatible with their method of obtaining 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 mold of casting.
  • 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 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 true EP0181255A1 (de) 1986-05-14
EP0181255B1 EP0181255B1 (de) 1987-12-23

Family

ID=9309108

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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1865258A1 (de) * 2006-06-06 2007-12-12 Siemens Aktiengesellschaft Gepanzerte Maschinenkomponente und Gasturbine
CN110723966A (zh) * 2019-11-13 2020-01-24 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

Families Citing this family (25)

* 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 (de) 2005-11-30 2019-08-21 Dresser-Rand Company Endverschlussvorrichtung für ein turbomaschinengehäuse
US8528339B2 (en) 2007-04-05 2013-09-10 Siemens Energy, Inc. Stacked laminate gas turbine component
WO2014120334A1 (en) * 2013-01-29 2014-08-07 Sippel Aaron D 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
EP2971577B1 (de) 2013-03-13 2018-08-29 Rolls-Royce Corporation Turbinendeckband
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
CA2915370A1 (en) 2014-12-23 2016-06-23 Rolls-Royce Corporation Full hoop blade track with axially keyed features
CA2915246A1 (en) 2014-12-23 2016-06-23 Rolls-Royce Corporation Turbine shroud
EP3045674B1 (de) 2015-01-15 2018-11-21 Rolls-Royce Corporation Turbinenummantelung mit rohrförmigen laufradpositionierungseinsätzen
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
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
US10415415B2 (en) 2016-07-22 2019-09-17 Rolls-Royce North American Technologies Inc. Turbine shroud with forward case and full hoop blade track
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

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL7216110A (de) * 1971-12-01 1973-06-05
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
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
FR2540938A1 (fr) * 1983-02-10 1984-08-17 Snecma Anneau de turbine d'une turbomachine

Family Cites Families (6)

* 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
US4112574A (en) * 1976-11-02 1978-09-12 International Harvester Company Torsielastic thrust bushing for track chains
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL7216110A (de) * 1971-12-01 1973-06-05
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
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
FR2540938A1 (fr) * 1983-02-10 1984-08-17 Snecma Anneau de turbine d'une turbomachine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1865258A1 (de) * 2006-06-06 2007-12-12 Siemens Aktiengesellschaft Gepanzerte Maschinenkomponente und Gasturbine
WO2007141091A1 (de) * 2006-06-06 2007-12-13 Siemens Aktiengesellschaft Gepanzerte maschinenkomponente und gasturbine
CN101473171B (zh) * 2006-06-06 2011-04-06 西门子公司 设有护甲的机器组件和燃气轮机
US8091366B2 (en) 2006-06-06 2012-01-10 Siemens Aktiengesellschaft Armor-plated machine components and gas turbines
CN110723966A (zh) * 2019-11-13 2020-01-24 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

Also Published As

Publication number Publication date
DE3561231D1 (en) 1988-02-04
EP0181255B1 (de) 1987-12-23
US4646810A (en) 1987-03-03
FR2572394B1 (fr) 1986-12-19
FR2572394A1 (fr) 1986-05-02
JPS61119370A (ja) 1986-06-06
JPH0247309B2 (de) 1990-10-19

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