Patent application number | Description | Published |
20090202381 | MATERIAL FOR COMPONENTS OF A GAS TURBINE - The presently described technology relates to a material for components of a gas turbine, in particular for components of a gas turbine aircraft engine, having a matrix of an iron-based alloy material, wherein the matrix of the iron-based alloy material being hardened by means of an intermetallic material of the Laves phase. | 08-13-2009 |
20140044549 | DUCTILE COMPENSATION LAYER FOR BRITTLE COMPONENTS - Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element ( | 02-13-2014 |
20140356644 | TiAl BLADE WITH SURFACE MODIFICATION - A component for a turbomachine having at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent. The intermetallic material is compacted and/or modified in microstructure by microplasticization at least partially at a surface or interface in a region close to the surface or interface. | 12-04-2014 |
20140369822 | Method for Producing Forged Components From A TiAl Alloy And Component Produced Thereby - The invention relates to a method for producing a component from a TiAl alloy, wherein the component is shaped by forging, in particular isothermal forging, and is subsequently subjected to at least one heat treatment, wherein in the first heat treatment the temperature is between 1100 and 1200° C. and is maintained for 6 to 10 hours and then the component is cooled. | 12-18-2014 |
20150086414 | CREEP-RESISTANT TiAl ALLOY - Disclosed is a TiAl alloy for high-temperature applications which comprises not more than 43 at. % of Al, from 3 at. % to 8 at. % of Nb, from 0.2 at. % to 3 at. % of Mo and/or Mn, from 0.05 at. % to 0.5 at. % of B, from 0.1 at. % to 0.5 at. % of C, from 0.1 at. % to 0.5 at. % of Si and Ti as balance. Also disclosed is a process for producing a component made of this TiAl alloy and the use of corresponding TiAl alloys in components of flow machines at operating temperatures up to 850° C. | 03-26-2015 |
20150315919 | LIGHTWEIGHT STRUCTURAL NiAl ALLOY WITH A HIGH HIGH-TEMPERATURE STRENGTH - Disclosed is a material on the basis of intermetallic nickel aluminides for applications which require a high high-temperature strength. The material comprises more than 50 at. % nickel and ternary Laves phases. Also disclosed is a component of a turbomachine produced from the material. | 11-05-2015 |
20160059312 | PRODUCTION PROCESS FOR TiAl COMPONENTS - The present invention relates to a process for producing a component, in particular a component for a turbomachine, composed of a TiAl alloy, which comprises the following:
| 03-03-2016 |
20160060734 | CREEP- AND OXIDATION-RESISTANT MOLYBDENUM SUPERALLOY - The present invention relates to a quaternary or multinary molybdenum alloy for the production of structural components, in particular of vanes of a turbomachine having the main constituents molybdenum, silicon, boron and titanium, which, as minor alloying elements, additionally comprises at least one of iron and yttrium. | 03-03-2016 |