Abstract: Ceramic abradable materials, in particular thermally sprayable ceramic abradable powder materials, and abradable seals formed by thermally spraying the materials include dysprosia (Dy2O3) and zirconia (ZrO2). Coatings are porous whereby the porosity, in part, is induced by plastic or fugitive phases. Abradable seal coatings comprising dysprosia and zirconia exhibit improved thermal shock and sintering resistance and can be worn into tolerance by untreated, bare turbine blades, at least in certain regimes of relative blade speed and coating porosity. Ceramic abradable seal coatings comprising dysprosia and zirconia can be used up to 1200° C.

Abstract: A ceramic abradable material is provided for use for clearance control between turbine blade tips and the shroud or casing in gas turbine engines for industrial and/or aerospace applications. The ceramic abradable material includes an yttria stabilized zirconia (YSZ) that is doped in alumina (Al2O3). The ceramic abradable in accordance with the invention is a soft abradable material that provides for increased erosion resistance as well as the ability of the turbine blade tips to cut into the abradable without causing them damage. These properties allow for optimum tolerances within the gas turbine engine which results in superior efficiency and performance.

Abstract: Ceramic abradable materials, in particular thermally sprayable ceramic abradable powder materials, and abradable seals formed by thermally spraying the materials include dysprosia (Dy2O3) and zirconia (ZrO2). Coatings are porous whereby the porosity, in part, is induced by plastic or fugitive phases. Abradable seal coatings comprising dysprosia and zirconia exhibit improved thermal shock and sintering resistance and can be worn into tolerance by untreated, bare turbine blades, at least in certain regimes of relative blade speed and coating porosity. Ceramic abradable seal coatings comprising dysprosia and zirconia can be used up to 1200° C.

Abstract: Method of applying a protective layer to a component made of an oxide dispersion hardened superalloy in which the surface of the component is subjected to heat treatment and/or provided with a coating before the protective layer is applied. This results in improved adhesive strength of the protective layer.

Abstract: A high-temperature protective layer on which a metal oxide-containing top layer forms under operating conditions. The high-temperature protective layer consists of an alloy which has an M-Cr-Al base material with which at least one metal of sub-group 4 or one transition metal of sub-group 5 of the periodic table and a metal-like material are alloyed. M represents a metallic element of sub-group 8 of the periodic table. This can be nickel, nickel/cobalt, cobalt or iron. The base material of the alloy contains silicon and zirconium or silicon and tantalum as additives.

Abstract: High-temperature protection layer of an alloy with a base of aluminum, chromium and nickel, particularly for structural gas-turbine elements of an austenitic material. The base material of the alloy contains at least 8 to 12 atom % aluminum and 28 to 28 atom % chromium with the remainder nickel, and at least silicon and titanium are admixed to the base material as additives such that at a temperature below 900.degree. C., a passive cover layer of chromium oxide, and at a temperature above 900.degree. C., a passive cover layer of aluminum oxide is developed on the applied alloy.

Abstract: High-temperature protection layer consisting of an alloy with a base of chromium, aluminum and cobalt, particularly for gas turbine parts of an austenitic material, characterized by the feature that at least silicon is admixed to the base material as an additive.

Abstract: The invention refers to a high temperature protective coating which is formed by an alloy of chromium, silicon, boron, iron and nickel. According to the invention, a light metal is mixed into the alloy as an additive. The additive consists preferably of aluminum. In addition, the silicon content of the high temperature protective coating is limited to 1.1 to 3.5 percent in weight relative to the total weight of the alloy.

Abstract: In a method for producing a high temperature alloy having increased creep strength, which comprises the steps of, forming a melt which consists essentially of 55-58 wt.% cobalt, 39-41 wt.% chromium, and 2.2-2.4 wt.% carbon; and solidifying said melt to obtain an alloy which is essentially a solid solution of chromium in cobalt as base alloy in which are embedded essentially parallel carbide filaments; the improvement is disclosed which comprises adding to said melt an amount of magnesium effective to deoxidize said alloy.

Abstract: In a cast anisotropic body comprising a monovariant ternary eutectic alloy of Co, Cr and C, which is segregated into a matrix, and a carbide dispersed phase, the matrix phase consisting essentially of a Co-Cr solid solution and the dispersed phase consisting essentially of a plurality of high strength carbide fibers oriented in substantial alignment and integrally embedded in the matrix phase, the improvement which comprises having contained in the matrix and/or dispersed phase, Ni in an amount of from 1.5 to 8.5 % by weight based on the total weight of the composition.