Abstract: A running-in coating for gas turbines and a method for production of a running-in coating are provided. The running-in coating serves to seal a radial gap between a housing (11) of the gas turbine and the rotating blades (10) themselves, whereby the running-in coating (13) is applied to the housing. The running-in coating is made from a CoNiCrAIY-hBN material. The CoNiCrAIY-hBN material can be applied by thermal spraying, in particular plasma spraying.

Abstract: A running-in coating for gas turbines and a method for production of a running-in coating are provided. The running-in coating serves to seal a radial gap between a housing (11) of the gas turbine and the rotating blades (10) themselves, whereby the running-in coating (13) is applied to the housing. The running-in coating is made from a CoNiCrAIY-hBN material. The CoNiCrAIY-hBN material can be applied by thermal spraying, in particular plasma spraying.

Abstract: A layer system for the rotor/stator seal of a turbomachine, in particular of a gas turbine, is applied to a metallic component and can be run in with respect to a further component which can move relative to the metallic component, which, in order to improve the service life and run-in properties, is characterized by a bonding layer which is applied to the metallic component and a run-in coating which is applied to the bonding layer and comprises at least two layers, the first layer, which adjoins the bonding layer, being harder than the second layer, and the second layer having run-in properties.

Abstract: A process for producing a thermal barrier coating, in which organometal complexes of zirconium and at least one stabilizing element selected from the group of the alkaline earth metals or rare earths are provided as starting substances, the starting substances are evaporated by heating and the coating gases that are generated in this manner are transported to a component to be coated, which is heated at a deposition temperature, where they are broken down so that a layer is deposited, in which process, in order to produce a thermal barrier coating with a columnar structure and a sufficient layer thickness, the starting substances are heated, at a process pressure of 0.5 to 50 mbar, to at most 250° C. so that the coating gases are formed, and the coating gases are transported to the component to be coated, the surface of which is heated at a deposition temperature of between 300° C. and 1100° C.

Abstract: A layer system for the rotor/stator seal of a turbomachine, in particular of a gas turbine, is applied to a metallic component and can be run in with respect to a further component which can move relative to the metallic component, which, in order to improve the service life and run-in properties, is characterized by a bonding layer which is applied to the metallic component and a run-in coating which is applied to the bonding layer and comprises at least two layers, the first layer, which adjoins the bonding layer, being harder than the second layer, and the second layer having run-in properties.

Abstract: A structural component made of a base metal composition on a nickel or cobalt basis is provided with a protective coating against oxidation, corrosion, and thermal fatigue. The protective coating and the base metal are made of chemically the same or identical material, whereby the bonding of the protective coating is increased, the tendency to crack is reduced, and the resistance to thermal fatigue is improved. The grain size of the coating is substantially smaller than the grain size of the base metal composition.

Abstract: A metal structure component is provided with a protective coating including three layers. A first layer on the surface of the metal structural component is a bond improving metallic base layer on which an intermediate heat insulating oxidic layer is applied, followed by a titanium fire inhibiting metallic cover layer. Due to this arrangement of three layers, it is possible for the advantageous characteristics of the individual layers to cooperate to provide a good bonding and heat insulating protection of the intermediate layer in combination with the titanium fire inhibiting protection of the outer layer, whereby the structural component achieves a prolonged operational life without a substantial weight increase as compared to conventional protection layers provided only for heat insulation purposes. This layer structure also minimizes any adverse influence on the structural strength of the metal structural component.

Abstract: A structural component which is coolable for use under high thermal load conditions, such as a turbine blade, has a metallic support core with cooling ducts separated by lands in its surface. The core and its cooling ducts and lands are enclosed by an inner layer of metal felt and an outer layer of heat insulating ceramic material which partially penetrates into the metal felt to form a bonding zone between the felt and the ceramic material. Thus, any heat passing through the ceramic layer is introduced into the large surface area of the metal felt enabling the latter to efficiently introduce the heat into a cooling medium flowing in the ducts, thereby preventing thermal loads from adversely affecting the metal core to any appreciable extent.

Abstract: For encapsulating a ceramic molded member for high-temperature isostatic pressing (HIP), a generally porous coating of glass and/or ceramic is applied on the molded member of ceramic and sintered under a vacuum into a pressure-tight capsule encompassing the molded member.