MATERIAL OF LAVES PHASE AND FERRITIC Fe-Al PHASE

Abstract

A material for components of a gas turbine, in particular a jet aircraft engine, is disclosed. The material contains an amount of a ferritic phase with Fe and Al and an amount of at least one Laves phase, where the amount of the at least one Laves phase constitutes the largest amount of the material.

What is claimed is: 
     
         1 . A material for a component of a gas turbine, comprising:
 an amount of a ferritic phase with Fe and Al; and   an amount of a Laves phase, wherein the amount of the Laves phase constitutes a largest amount of the material.   
     
     
         2 . The material according to  claim 1 , wherein the amount of the Laves phase is greater than or equal to 50% by volume. 
     
     
         3 . The material according to  claim 1 , wherein the Laves phase is a ternary or multinary Laves phase. 
     
     
         4 . The material according to  claim 3 , wherein the ternary or multinary Laves phase is formed on a basis of FeTaAl. 
     
     
         5 . The material according to  claim 4 , wherein the Laves phase based on FeTaAl additionally comprises Nb, which partially replaces Ta. 
     
     
         6 . The material according to  claim 3 , wherein the ternary or multinary Laves phase is formed on a basis of FeNbAl. 
     
     
         7 . The material according to  claim 6 , wherein the Laves phase based on FeNbAl additionally comprises Ta, which partially replaces Nb. 
     
     
         8 . The material according to  claim 1 , wherein the Laves phase contains Cr, which partially replaces Fe. 
     
     
         9 . The material according to  claim 1 , wherein the Laves phase is formed on a basis of FeCrAlTaNb. 
     
     
         10 . The material according to  claim 1 , wherein the ferritic phase additionally comprises Cr. 
     
     
         11 . The material according to  claim 1 , wherein the Laves phase in a material structure forms a matrix or a skeleton and wherein the ferritic phase is incorporated into the matrix or the skeleton. 
     
     
         12 . The material according to  claim 1 , wherein the material comprises up to 45 atomic percent (at. %) Al and up to 25 atomic percent (at. %) Ta and/or Nb and/or up to 25 atomic percent (at. %) Cr. 
     
     
         13 . The material according to  claim 1 , wherein the material comprises 20 to 25 atomic percent (at. %) Cr, 5 to 35 atomic percent (at. %) Al, and 10 to 25 atomic percent (at. %) tantalum and/or niobium as well as a remainder being Fe and unavoidable impurities. 
     
     
         14 . The material according to  claim 1 , wherein the material comprises more than 35 atomic percent (at. %) Al and Cr less than or equal to 10 atomic percent (at. %). 
     
     
         15 . The material according to  claim 1 , wherein the material is produced by a melt metallurgy method or a powder metallurgy method. 
     
     
         16 . The material according to  claim 1 , wherein the gas turbine is a jet aircraft engine. 
     
     
         17 . A component of a gas turbine comprising a material according to  claim 1 . 
     
     
         18 . The component according to  claim 17 , wherein the gas turbine is a jet aircraft engine.