Abstract: A method produces thermal barrier coatings that adhere to components even at high temperatures and temperatures that change frequently. A gas-tight glass-metal composite coating is applied to the component and annealed. The corroded part of the gas-tight coating is then removed, and a second, porous coating is applied. The second coating can comprise a ceramic, in particular yttrium-stabilized zirconium oxide. A thermal barrier coating is provided that is a composite made of a gas-tight glass-metal composite coating and another porous coating disposed thereover. Because the boundary volume of the composite coating is partly crystallized to the other coating, superior adhesion within the composite is achieved. Thus, it is in particular possible to produce a composite made of silicate glass-metal composite coatings and yttrium-stabilized zirconium oxide that are temperature-stable for extended periods of time.

Abstract: A heat-insulating material has a first phase with the stoichiometric composition of 0.1 to 10 mol-% M12O3, 0.1 to 10 mol-% Li2O, and as the remainder M22O3 with possible impurities. M1 is selected from the elements lanthanum, neodymium, gadolinium, or a mixture thereof, and M2 is selected from the elements aluminum, gallium, iron, or a mixture thereof. The first phase is present in a magnetoplumbite structure.

Abstract: A heat-insulating layer has a melting point above 2500° C., a thermal expansion coefficient in excess of 8×10?6 K?1, and a sintering temperature greater than 1400° C. This material has a perovskite structure of the general formula A1+r(B?1/2+xB?1/2+y)O3+z in which: A=at least one element of the group (Ba, Sr, Ca, Be), B?=at least one element of the group (Al, La, Nd, Gd, Er, Lu, Dy, Tb), B?=at least one element of the group (Ta, Nb), and 0.1<r,x,y,z<0.1.

Abstract: The aim of the invention is to produce complete high temperature fuel cells by means of thermal injection processes (e.g. atmospheric plasma injection, vacuum plasma injection, high speed flame injection). The production method is especially simplified and is economical by virtue of the fact that the carrier substrate is also produced on a base with the aid of a thermal injection method. The base or an intermediate layer placed thereon can be advantageously dissolved or decomposed such that the carrier substrate provided with layers arranged thereon can be separated in a very simple manner from the base which becomes unnecessary. Said method advantageously enables the production of all layers of a high temperature fuel cell, exclusively with the aid of a thermal injection method.

Abstract: A method produces thermal barrier coatings that adhere to components even at high temperatures and temperatures that change frequently. A gas-tight glass-metal composite coating is applied to the component and annealed. The corroded part of the gas-tight coating is then removed, and a second, porous coating is applied. The second coating can comprise a ceramic, in particular yttrium-stabilized zirconium oxide. A thermal barrier coating is provided that is a composite made of a gas-tight glass-metal composite coating and another porous coating disposed thereover. Because the boundary volume of the composite coating is partly crystallized to the other coating, superior adhesion within the composite is achieved. Thus, it is in particular possible to produce a composite made of silicate glass-metal composite coatings and yttrium-stabilized zirconium oxide that are temperature-stable for extended periods of time.

Abstract: A heat-insulating layer has a melting point above 2500° C., a thermal expansion coefficient in excess of 8×10?6 K?1, and a sintering temperature greater than 1400° C. This material has a perovskite structure of the general formula A1+r(B?1/2+xB?1/2+y)O3+z in which: A=at least one element of the group (Ba, Sr, Ca, Be), B?=at least one element of the group (Al, La, Nd, Gd, Er, Lu, Dy, Tb), B?=at least one element of the group (Ta, Nb), and 0.1<r, x, y, z<0.1.

Abstract: A heat-insulating material has a melting point above 2500° C., a thermal expansion coefficient in excess of 8×10?6 K?1, and a sintering temperature greater than 1400° C. It has a perovskite structure of the general formula A1+r(B?1/3+xB?2/3+y)O3+z where A=at least one element of the group (Ba, Sr, Ca, Be), B?=at least one element of the group (Mg, Ca, Sr, Ba, Be), B?=at least one element of the group (Ta, Nb), r, x, and z?0, and ?0.1<r, x, y, z<0.1; or of the general formula A1+r(B?1/2+xB?1/2+y)O3+z where A and B? are as above and B?=at least one element of the group (Al, La, Nd, Gd, Er, Lu, Dy, Tb), and ?1.0<r, x, y, z<0.1.

Abstract: The invention relates to a heat-insulating material, which is phase-stable particularly for high temperatures above 1150° C., especially above 1200° C., and which has a very good long-time stability. The heat-insulating material can exist in a number of phases of which at least one has the magnetoplumbite structure and stoichiometrically contains 0.1 to 10 mol % M12O3, 0.1 to 10 mol % Li2O and, as the remaining, M22O3 with incidental impurities. M1 is selected from the following elements: lanthanum, neodymium and gadolinium or mixtures thereof, and M2 is selected from the following elements: aluminum, gallium, iron or a mixture thereof. A particularly advantageous composition arises for this phase with the composition LaLiAl11O18.5 or LaLi0.5Al11.5O19. By using conventional methods, the heat-insulating material can be applied to the components subjected to a high level of thermal stress, for example, turbine blades.

Abstract: A heat-insulating layer system for a metallic structural component, especially for a structural component of a gas turbine such as an aircraft engine, includes an adhesion promoting layer (12), an inner contact layer (14), and an outer cover layer (15) , whereby the adhesion promoting layer (12). is disposed on a surface (11) of the gas turbine structural component (10). The inner contact layer (14) is formed of a zirconium oxide partially stabilized with yttrium or yttrium oxide, and the outer cover layer (15) is formed of a material that consists of at least one component with at least one phase, which stoichiometrically comprises 1 to 80 Mol-% Mx2O3, 0.5 to 80 Mol-% MyO and Al2O3 as a remainder with incidental impurities, wherein Mx is selected from the elements chromium and barium or mixtures thereof, and wherein My is selected from the alkaline earth metals, the transition metals and the rare earths or mixtures thereof.

Abstract: The invention relates to a method for producing a tight crystalline mullite layer on a metallic and/or ceramic substrate by using the plasma spraying technique. To this end, a sol containing mullite precursors with a proportion of 2 to 25% by weight with regard to the oxides (3 Al2O3/2 SiO2) is used as a spraying additive. This method is carried out under atmospheric conditions, and the sol is injected with a focussed jet and with an overpressure of at least one I bar into the plasma flame. An additional compacting of the layer can be advantageously effected by repeatedly passing over the layer with the plasma flame. The method is particularly suited for applying a gas-tight crystalline mullite layer to a steel substrate.

Abstract: The invention relates to a method for the production of a thin dense ceramic layer on a substrate by means of atmospheric plasma spraying, whereby the following steps are carried out: a) the substrate is pre-heated to a temperature corresponding to at least a quarter of the melting point of the ceramic for application in Kelvin, b) a ceramic powder or a ceramic powder mixture with d50-values of less than 50 gm is used as spray adjunct, c) particle speeds at incidence on the substrate of more than 200 m/s are set, d) particle temperatures are set such that on incidence on the substrate surface the particles have a temperature at least 5% above the melting point of the ceramic for application in Kelvin, e) the amount of the spray adjunct and passage speed of the plasma burner are set such that on a single pass of the substrate a layer thickness of less than 100 ?m is achieved, f) a thin and also gas-tight layer is generated on the substrate with a single pass of the substrate which has a leakage rate of less th

Abstract: The invention relates to a heat-insulating layer system for metallic structural components, especially for structural components of a gas turbine such as an aircraft engine. The heat-insulating layer system (13) comprises an inner contact layer (14) and an outer cover layer (15), whereby the inner contact layer (14) is applied onto a surface (11) of a gas turbine structural component (10) with intermediate arrangement of an adhesion promoting layer (12). According to the invention, the inner contact layer (14) is formed of a zirconium oxide partially stabilized with yttrium or yttrium oxide, the outer cover layer (15) is formed of lanthanum hexaaluminate.

Abstract: The aim of the invention is to produce complete high temperature fuel cells by means of thermal injection processes (e.g. atmospheric plasma injection, vacuum plasma injection, high speed flame injection). The production method is especially simplified and is economical by virtue of the fact that the carrier substrate is also produced on a base with the aid of a thermal injection method. The base or an intermediate layer placed thereon can be advantageously dissolved or decomposed such that the carrier substrate provided with layers arranged thereon can be separated in a very simple manner from the base which becomes unnecessary. Said method advantageously enables the production of all layers of a high temperature fuel cell, exclusively with the aid of a thermal injection method.

Abstract: The invention relates to a heat-insulating layer made of a heat-insulating material which has a complex perovskite structure, having a melting point greater than 2500° C. and a thermal coefficient of expansion greater than 8*10?6 K?1 in addition to a sintering temperature of more than 1400° C. The inventive heat insulating material is characterised by a first general formula A1+r(B?1/3+xB?2/3+y)03+2, wherein: A=at least one element from the group (Ba, Sr, Ca, Be), B?=at least one element from the group (Mg, Ca, Sr, Ba, Be), B?=at least one element from the group (Ta, Nb) and ?0.1<r, x, y, z<0,1; or by a second general formula A1+r(B?1/2+x, B?1/2 +y)03 +2, wherein: A =at least one element from the group (Ba, Sr, Ca, Be), B?=at least one element from the group (Al, La, Nd, Gd, Er, Lu, Dy, Th), B?=at least one element from the group (Ta, Nb) and ?0, 1<r, x, y, z<0,1.

Abstract: The invention relates to a material, in particular for a thermal insulation layer, with increased thermal stability, a low heat conductivity and a large thermal coefficient of expansion. According to the invention, said material comprises lanthanides, in particular the elements La, Ce, Nd, Yb, Lu, Er or Tm, which preferably occur as a mixture in a Perovskite structure. Said thermal insulation layer is particularly suitable for replacing thermal insulation layers comprising yttrium stabilized zirconium oxides (YSZ) as the thermal stability thereof is given as well over 1200° C.

Abstract: The invention relates to a heat insulating layer on a metallic substrate for using for high temperatures, especially for temperatures above 1300° C. Starting with a base of La2Zr2O7, the properties of the heat insulating substance to be used as the heat insulating layer are regularly improved, by substituting lanthanum cations with ions of elements Nd, Eu, Dy, Sm and/or Gd. An additional, at least partial substitution of the zirconium cations by Ce, Hf or Ta is advantageous. Improving the properties results especially in a high thermal coefficient of dilation &agr; and low heat conductivity &lgr;.

Abstract: The invention relates to a material, in particular for a thermal insulation layer, with increased thermal stability, a low heat conductivity and a large thermal coefficient of expansion. According to the invention, said material comprises lanthanides, in particular the elements La, Ce, Nd, Yb, Lu, Er or Tm, which preferably occur as a mixture in a Perovskite structure. Said thermal insulation layer is particularly suitable for replacing thermal insulation layers comprising yttrium stabilised zirconium oxides (YSZ) as the thermal stability thereof is given as well over 1200° C.

Abstract: The invention discloses a component with a heat-insulating layer on its surface. The heat-insulating layer comprises a lower region and an upper region. The lower region is situated between the component and the upper region. The lower region consists entirely or predominantly of YSZ or a glass-metal composite material.

Abstract: In a dispersoid-reinforced electrode with a net-like open pore structure and a ceramic and a metallic meshwork, ceramic particles with an average particle diameter of less than 100 nm are homogeneously distributed in the metallic network thereby reinforcing the electrode.