DE3235230A1 - Gas turbine blade having a metal core and a ceramic vane - Google Patents

Gas turbine blade having a metal core and a ceramic vane

Info

Publication number
DE3235230A1
DE3235230A1 DE19823235230 DE3235230A DE3235230A1 DE 3235230 A1 DE3235230 A1 DE 3235230A1 DE 19823235230 DE19823235230 DE 19823235230 DE 3235230 A DE3235230 A DE 3235230A DE 3235230 A1 DE3235230 A1 DE 3235230A1
Authority
DE
Germany
Prior art keywords
ceramic
metal
gas turbine
turbine blade
core
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
DE19823235230
Other languages
German (de)
Other versions
DE3235230C2 (en
Inventor
Werner Dr.-Ing. 8047 Karlsfeld Hüther
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.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Priority to DE19823235230 priority Critical patent/DE3235230A1/en
Publication of DE3235230A1 publication Critical patent/DE3235230A1/en
Application granted granted Critical
Publication of DE3235230C2 publication Critical patent/DE3235230C2/de
Granted legal-status Critical Current

Links

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
    • 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
    • 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
    • F01D5/284—Selection of ceramic materials

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Ceramic Products (AREA)

Abstract

A gas turbine blade having a metallic core, connected to a rotor disc, and a ceramic profiled vane surrounding said core at a distance, a metallic felt (2) being inserted between the metallic core (1) and the ceramic sleeve (3). <IMAGE>

Description

Gasturbinenschaufel mit Metallkern Gas turbine blade with a metal core

und Keramikblatt Die Erfindung bezieht sich auf eine Gasturbinenschaufel mit einem mit einer Laufscheibe verbundenen metallischen Kern und einem diesen Kern mit Abstand umhüllenden Profilblatt aus Keramik. Solche Verbundschaufeln sind gegenüber reinen Metallschaufeln bei höheren Temperaturen verwendbar und weisen erhöhte Erosionsfestigkeit auf. and ceramic blade. The invention relates to a gas turbine blade with a metallic core connected to a running disk and this core at a distance enveloping profile sheet made of ceramic. Such composite blades are opposite Pure metal blades can be used at higher temperatures and have increased resistance to erosion on.

Beim Betrieb solcher Schaufeln kommt es immer wieder vor, daß durch Feststoffteile etwa in Form von Koksstücken, die sich aus der Brennkammer ablösen und auf die Beschaufelung auftreffen, ein Keramikprofilblatt bricht und die wegfliegenden Keramikstücke zu ernsten Folgeschäden führen.When operating such blades it happens again and again that by Solid parts, for example in the form of pieces of coke, which are detached from the combustion chamber and hit the blading, breaking a ceramic profile sheet and flying away Ceramic pieces lead to serious consequential damage.

Aufgabe der vorliegenden Erfindung ist es, eine gattungsgemäße Gasturbinenschaufel zu schaffen, bei der die Gefahr von Folgeschäden beim Bruch des Keramikblattes weitgehend ausgeschlossen ist.The object of the present invention is to provide a generic gas turbine blade to create at which the risk of consequential damage if the ceramic sheet breaks to a large extent is excluded.

Zur Lösung dieser Aufgabe wird erfindungsgemäß vorgeschlagen, daß, wie für ein Metallkeramikbauteil an sich bekannt, zwischen Metallkern und Keramikhülle ein Metallfilz eingesetzt ist, der jeweils an den Grenzflächen mit dem Metall und mit der Keramik, vorzugsweise durch Löten unlösbar verbunden ist.To solve this problem it is proposed according to the invention that, as for a metal-ceramic component itself known between metal core and ceramic shell a metal felt is inserted, each at the interfaces permanently connected to the metal and to the ceramic, preferably by soldering is.

Zwar ist es aus der DE-OS 30 14 645 bekannt, bei einem Metallkeramikbauteil zwischen Keramik und Metall einen Metallfilz einzusetzen, der mit dem Metall und dem Keramik vorzugsweise durch Löten unlösbar verbunden ist.It is known from DE-OS 30 14 645 for a metal-ceramic component insert a metal felt between ceramic and metal, which with the metal and the ceramic is preferably permanently connected by soldering.

Bei dem vorbekannten, vorzugsweise rotationssymmetrischen Bauteil soll durch diesen Aufbau jedoch das Problem der unterschiedlichen Wärmedehnung zwischen Keramik und Metall gelöst werden. Einen Hinweis auf die Verwendung eines solchen Aufbaues für eine Gasturbinenschaufel gibt die vorveröffentlichte Druckschrift nicht.In the previously known, preferably rotationally symmetrical component should by this structure, however, the problem of different thermal expansion between Ceramic and metal are dissolved. An indication of the use of such a The previously published document does not provide any structure for a gas turbine blade.

Der Hauptvorteil einer erfindungsgemäß aufgebauten Gasturbinenschaufel liegt darin, daß beim Bruch des Keramikprofil blattes etwa durch Aufschlag eines Fremdkörpers keine großen Bruchstücke davonfliegen können, da durch die unlösbare Verbindung mit dem Metallfilz die Bruchstücke am Metall kern gehalten werden.The main advantage of a gas turbine blade constructed in accordance with the invention lies in the fact that when the ceramic profile sheet breaks, for example by impact of a Foreign bodies cannot fly away large fragments because they cannot be removed Connection with the metal felt, the fragments are held on the metal core.

In der beigefügten Zeichnung ist eine erfindungsgemäße Gasturbinenschaufel im Querschnitt dargestellt. Diese Gasturbinenschaufel besteht aus einem Metallkern 1 mit Tannenbaumfuß Ii und einer zentralen Kühlluftbohrung 12.In the accompanying drawing is a gas turbine blade according to the invention shown in cross section. This gas turbine blade consists of a metal core 1 with a fir tree base Ii and a central cooling air hole 12.

Den Metall kern 1 umgibt allseitig ein Metallfilz 2, an den sich nach außen ein Keramikprofilblatt 3 anschließt.The metal core 1 surrounds on all sides a metal felt 2, which is after outside a ceramic profile sheet 3 connects.

Der Metallfilz 2 ist mit dem Metall kern 1 und dem Keramikprofilblatt 3 durch Lötung unlösbar verbunden. Diese Verbindung kann eine weitere Sicherung des Keramikprofilblattes am Metallkern überflüssig machen, wie es aus dem gezeigten Ausführungsbeispiel hervorgeht. Dadurch ergibt sich eine beträchtliche Herstellungsvereinfachung für Metallkeramikverbundschaufeln, da aufwendige Verbindungstechniken zwischen Keramikblatt und Metallkern entfallen. Bevorzugt verwendete Keramikmaterialien sowie Material für den Metallfilz sind in den Patentansprüchen 2 und 3 angegeben.The metal felt 2 is with the metal core 1 and the ceramic profile sheet 3 permanently connected by soldering. This connection can be another backup of the ceramic profile sheet on the metal core, like it the end is apparent from the embodiment shown. This results in a considerable Manufacturing simplification for metal-ceramic composite blades, since complex connection techniques between the ceramic blade and the metal core are omitted. Ceramic materials preferably used and the material for the metal felt are specified in claims 2 and 3.

Claims (3)

Patentansprüche 1Gasturbinenschaufel mit einem mit einer Laufscheibe verbundenen metallischen Kern und einem diesen Kern mit Abstand umhüllenden Profilblatt aus Keramik, dadurch gekennzeichnet, daß, wie für ein Metall keramikbauteil an sich bekannt, zwischen Metall kern (1) und Keramikhülle (3) ein Metallfilz (2) eingesetzt ist, der jeweils an den Grenzflächen mit dem Metall und mit der Keramik, vorzugsweise durch Löten, unlösbar verbunden ist. Claims 1 Gas turbine blade with one with a rotor disk connected metallic core and a profile sheet enveloping this core at a distance made of ceramic, characterized in that, as for a metal, ceramic component per se known, a metal felt (2) used between metal core (1) and ceramic shell (3) is, in each case at the interfaces with the metal and with the ceramic, preferably is permanently connected by soldering. 2. Gasturbinenschaufel nach Anspruch 1, > dadurch gekennzeichnet, daß als Keramikmaterial Siliziumnitrid, Siliziumkarbid, vorzugsweise drucklos gesintertes Siliziumkarbid verwendet wird.2. Gas turbine blade according to claim 1,> characterized in that that the ceramic material silicon nitride, silicon carbide, preferably sintered without pressure Silicon carbide is used. 3. Gasturbinenschaufel nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß als Material für den Metallfilz hochwarmfeste Nickelbasislegierungen, wie z. B. IN lOOR, Udimet 700R und IN 718R verwendet werden.3. Gas turbine blade according to claim 1 or 2, characterized in that that as a material for the metal felt high-temperature nickel-based alloys, such as. B. IN lOOR, Udimet 700R and IN 718R can be used.
DE19823235230 1982-09-23 1982-09-23 Gas turbine blade having a metal core and a ceramic vane Granted DE3235230A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19823235230 DE3235230A1 (en) 1982-09-23 1982-09-23 Gas turbine blade having a metal core and a ceramic vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19823235230 DE3235230A1 (en) 1982-09-23 1982-09-23 Gas turbine blade having a metal core and a ceramic vane

Publications (2)

Publication Number Publication Date
DE3235230A1 true DE3235230A1 (en) 1984-03-29
DE3235230C2 DE3235230C2 (en) 1990-04-19

Family

ID=6173961

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19823235230 Granted DE3235230A1 (en) 1982-09-23 1982-09-23 Gas turbine blade having a metal core and a ceramic vane

Country Status (1)

Country Link
DE (1) DE3235230A1 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0132667A1 (en) * 1983-07-28 1985-02-13 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Thermally highly stressed cooled turbine blade
WO2002027145A2 (en) * 2000-09-29 2002-04-04 Siemens Westinghouse Power Corporation Vane assembly for a turbine and combustion turbine with this vane assembly
US6412541B2 (en) 2000-05-17 2002-07-02 Alstom Power N.V. Process for producing a thermally loaded casting
US6499943B1 (en) 1999-08-09 2002-12-31 Alstom (Switzerland Ltd Friction-susceptible component of a thermal turbo machine
WO2006074949A1 (en) * 2005-01-14 2006-07-20 Cvrd Inco Limited Turbine blade for turbo-engines and method for manufacturing same
EP2322762A1 (en) * 2009-11-12 2011-05-18 Siemens Aktiengesellschaft Modular turbine component and method for its manufacture
EP3239469A1 (en) * 2014-11-20 2017-11-01 Rolls-Royce North American Technologies, Inc. Composite blades for gas turbine engines

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100430499C (en) 2002-08-16 2008-11-05 阿尔斯托姆科技有限公司 Intermetallic material and use of said material

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2822627A1 (en) * 1978-05-24 1979-11-29 Volkswagenwerk Ag CERANOX COMPOUND AND METHOD OF MANUFACTURING IT
DE2945531B1 (en) * 1979-11-10 1981-05-14 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbo blade with a matt core and a ceramic blade
DE3014645A1 (en) * 1980-04-16 1981-10-22 MTU Motoren- und Turbinen-Union München GmbH, 8000 München METAL-CERAMIC COMPONENT AND METHOD FOR THE PRODUCTION THEREOF

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2822627A1 (en) * 1978-05-24 1979-11-29 Volkswagenwerk Ag CERANOX COMPOUND AND METHOD OF MANUFACTURING IT
DE2945531B1 (en) * 1979-11-10 1981-05-14 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbo blade with a matt core and a ceramic blade
DE3014645A1 (en) * 1980-04-16 1981-10-22 MTU Motoren- und Turbinen-Union München GmbH, 8000 München METAL-CERAMIC COMPONENT AND METHOD FOR THE PRODUCTION THEREOF

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
JP 54-67817 A. In: Patents Abstra. of Japan, Sect. M., Vol. 3, 1979, Nr. 93 (M-68) *

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0132667A1 (en) * 1983-07-28 1985-02-13 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Thermally highly stressed cooled turbine blade
US6499943B1 (en) 1999-08-09 2002-12-31 Alstom (Switzerland Ltd Friction-susceptible component of a thermal turbo machine
EP1076157A3 (en) * 1999-08-09 2004-01-02 ALSTOM (Switzerland) Ltd Friction element for a turbomachine
US6412541B2 (en) 2000-05-17 2002-07-02 Alstom Power N.V. Process for producing a thermally loaded casting
WO2002027145A2 (en) * 2000-09-29 2002-04-04 Siemens Westinghouse Power Corporation Vane assembly for a turbine and combustion turbine with this vane assembly
WO2002027145A3 (en) * 2000-09-29 2003-12-11 Siemens Westinghouse Power Vane assembly for a turbine and combustion turbine with this vane assembly
WO2006074949A1 (en) * 2005-01-14 2006-07-20 Cvrd Inco Limited Turbine blade for turbo-engines and method for manufacturing same
EP2322762A1 (en) * 2009-11-12 2011-05-18 Siemens Aktiengesellschaft Modular turbine component and method for its manufacture
WO2011058043A1 (en) * 2009-11-12 2011-05-19 Siemens Aktiengesellschaft Modular turbine component and method for the production thereof
EP3239469A1 (en) * 2014-11-20 2017-11-01 Rolls-Royce North American Technologies, Inc. Composite blades for gas turbine engines
US10180071B2 (en) 2014-11-20 2019-01-15 Rolls-Royce North American Technologies Inc. Composite blades for gas turbine engines

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Legal Events

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8110 Request for examination paragraph 44
D2 Grant after examination
8364 No opposition during term of opposition
8339 Ceased/non-payment of the annual fee