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: 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 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 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;.