EP1966405A1 - Materiau pour composants de turbine a gaz - Google Patents

Materiau pour composants de turbine a gaz

Info

Publication number
EP1966405A1
EP1966405A1 EP06828670A EP06828670A EP1966405A1 EP 1966405 A1 EP1966405 A1 EP 1966405A1 EP 06828670 A EP06828670 A EP 06828670A EP 06828670 A EP06828670 A EP 06828670A EP 1966405 A1 EP1966405 A1 EP 1966405A1
Authority
EP
European Patent Office
Prior art keywords
iron
gas turbine
components
intermetallic
material 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.)
Ceased
Application number
EP06828670A
Other languages
German (de)
English (en)
Inventor
Wilfried Smarsly
Gerhard Sauthoff
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 AG
Original Assignee
Max Planck Institut fuer Eisenforschung
MTU Aero Engines 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 Max Planck Institut fuer Eisenforschung, MTU Aero Engines GmbH filed Critical Max Planck Institut fuer Eisenforschung
Publication of EP1966405A1 publication Critical patent/EP1966405A1/fr
Ceased legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/002—Ferrous alloys, e.g. steel alloys containing In, Mg, or other elements not provided for in one single group C22C38/001 - C22C38/60
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/005—Ferrous alloys, e.g. steel alloys containing rare earths, i.e. Sc, Y, Lanthanides
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/06—Ferrous alloys, e.g. steel alloys containing aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/12—Ferrous alloys, e.g. steel alloys containing tungsten, tantalum, molybdenum, vanadium, or niobium

Definitions

  • the invention relates to a material for components of a gas turbine.
  • Modern gas turbines in particular aircraft engines, must meet the highest demands in terms of reliability, weight, performance, economy and service life.
  • the most important materials used today for aircraft engines or other gas turbines are titanium alloys, nickel alloys and high-strength steels.
  • the high strength steels are used for shaft parts, gear parts, compressor casings and turbine casings.
  • Titanium alloys are typical materials for compressor parts.
  • Nickel alloys are suitable for the hot turbine parts of an aircraft engine.
  • ODS materials oxide dispersion reinforced superalloys
  • CMC materials ceramic matrix composite materials
  • intermetallic NiAl materials or intermetallic TiAl materials are relatively expensive, so there is a need for a novel material suitable for gas turbine components exposed to temperatures in excess of 900 ° C.
  • the present invention is based on the problem of creating a novel material for components of a gas turbine.
  • the material according to the invention has a matrix of an iron-base alloy material, wherein the matrix of the iron-base alloying material is cured with an intermetallic material of the Laves phase.
  • the material according to the invention represents a cost-effective alternative for the materials known from the prior art and is primarily suitable for gas turbine components which are exposed to temperatures above 900 ° C. With the help of the material according to the invention component costs of gas turbine components can be reduced.
  • the material preferably comprises 70.0 to 99.9% by volume of the iron-base alloying material and 0.1 to 30.0% by volume of the Laves phase intermetallic material.
  • the present invention provides a novel material for components of a gas turbine, namely for components of Gasturbinenflugtriebwer- ken, which are exposed during operation temperatures of preferably more than 900 ° C.
  • the material according to the invention has a matrix of an iron-base alloy material, the matrix of the iron-based alloy material having been hardened with an intermetallic material of the Laves phase.
  • a Laves phase is a hexagonal intermetallic phase.
  • the interlave material of the Laves phase is embedded in the matrix of the iron-based alloy material, wherein the material according to the invention preferably has the following composition:
  • the iron-base alloy material of the matrix of the material according to the invention contains at least iron (Fe), aluminum (Al), chromium (Cr), yttrium (Y) and / or hafnium (Hf).
  • the iron-base alloy material of the matrix of the material according to the invention has the following composition:
  • the LaVes phase intermetallic material used to cure the matrix contains at least iron (Fe), aluminum (Al), niobium (Nb) and / or tantalum (Ta).
  • This Laves phase intermetallic material preferably has the following composition:
  • the invention relates to a component of a gas turbine, preferably a gas turbine aircraft engine, which is made of such a material.
  • the material according to the invention is particularly suitable for the production of housings such as combustion chamber housings, high-pressure compressor housings and low-pressure turbine housings.
  • the material according to the invention is suitable for producing exhaust gas guides, diffuser components, brush seals and sealing elements which are used in the inner-air-seal area and outer-air-seal area of a turbine, in particular a low-pressure turbine or a compressor of a gas turbine aircraft engine.

Abstract

L'invention concerne un matériau pour composants de turbine à gaz, en particulier pour composants de moteurs d'avion à turbine à gaz, qui présente une matrice en un matériau d'alliage à base de fer. La matrice en matériau d'alliage à base de fer est durcie par un matériau intermétallique de la phase de Laves.
EP06828670A 2005-12-23 2006-12-15 Materiau pour composants de turbine a gaz Ceased EP1966405A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005061790A DE102005061790A1 (de) 2005-12-23 2005-12-23 Werkstoff für Bauteile einer Gasturbine
PCT/DE2006/002239 WO2007076805A1 (fr) 2005-12-23 2006-12-15 Materiau pour composants de turbine a gaz

Publications (1)

Publication Number Publication Date
EP1966405A1 true EP1966405A1 (fr) 2008-09-10

Family

ID=37890904

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06828670A Ceased EP1966405A1 (fr) 2005-12-23 2006-12-15 Materiau pour composants de turbine a gaz

Country Status (5)

Country Link
US (1) US8012271B2 (fr)
EP (1) EP1966405A1 (fr)
JP (1) JP2009520877A (fr)
DE (1) DE102005061790A1 (fr)
WO (1) WO2007076805A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2840154A1 (fr) * 2013-08-21 2015-02-25 MTU Aero Engines GmbH Procédé de fabrication de composants issus de, et avec des, phases de Laves
EP2840158A1 (fr) 2013-08-21 2015-02-25 MTU Aero Engines GmbH Alliage FeAlCr ferritique avec des phases de Laves ternaires et avec des oxides et/ou des carbides pour des composants d'une turbine à gaz
ES2634089T3 (es) 2013-11-22 2017-09-26 MTU Aero Engines AG Material que consta de fase Laves y fase Fe-Al ferrítica

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR920010422B1 (ko) * 1987-05-15 1992-11-27 마쯔시다덴기산교 가부시기가이샤 수소흡수저장전극 및 그 제조법
EP0533059B1 (fr) 1991-09-19 1997-01-02 Hitachi Metals, Ltd. Superalliage à faible coefficient de dilatation thermique
JP3135691B2 (ja) * 1991-09-19 2001-02-19 日立金属株式会社 低熱膨張超耐熱合金
JP3289847B2 (ja) * 1993-02-05 2002-06-10 日立金属株式会社 耐酸化性に優れた低熱膨張超耐熱合金
JP3982069B2 (ja) * 1998-07-08 2007-09-26 住友金属工業株式会社 高Ｃｒフェライト系耐熱鋼
DE19928842C2 (de) * 1999-06-24 2001-07-12 Krupp Vdm Gmbh Ferritische Legierung
JP4288821B2 (ja) * 2000-02-28 2009-07-01 日立金属株式会社 高温強度に優れた低熱膨張Ｆｅ基耐熱合金
JP4304109B2 (ja) * 2004-04-02 2009-07-29 新日鐵住金ステンレス株式会社 熱疲労特性に優れた自動車排気系部材用フェライト系ステンレス鋼

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
SCHNEIDER ANDRE ET AL: "Iron Aluminium Alloys with Strengthening Carbides and Intermetallic Phases for High-Temperature Applications", STEEL RESEARCH INTERNATIONAL, VERLAG STAHLEISEN GMBH., DUSSELDORF, DE, vol. 75, no. 1, 1 January 2004 (2004-01-01), pages 55 - 61, XP009093993, ISSN: 1611-3683 *

Also Published As

Publication number Publication date
US8012271B2 (en) 2011-09-06
JP2009520877A (ja) 2009-05-28
US20090202381A1 (en) 2009-08-13
DE102005061790A1 (de) 2007-07-05
WO2007076805A1 (fr) 2007-07-12

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