Abstract: The invention relates to a method for producing a ceramic core (4, 4?)—and to a core produced by this method—for preparing the production of a casting having hollow structures which the ceramic core is configured to form, making use of a 3D model of digital geometric co-ordinates of the casting, wherein the method comprises the following steps: a) Producing by means of casting technology at least one first portion (4) of the ceramic core including at least one first joining structure (24) in a surface of the portion; b) Producing by means of casting technology or 3D printing technology at least one second portion (4?) of the ceramic core including at least one second joining structure (26) matching the first joining structure, in a surface of the portion, wherein the production by means of casting technology comprises the following steps: i. Unpressurized or low-pressure casting of a ceramic core blank, and specifically with an oversize relative to the core (4, 4?) according to the geometric co-ordinates; ii.

Abstract: A method for producing a ceramic core, and such a core, for preparing the production of a casting having hollow structures. The ceramic core configured to form, making use of a 3D model of digital geometric co-ordinates of the casting. The method involves unpressurized or low-pressure casting of a ceramic core blank, and specifically with an oversize relative to the core according to the geometric co-ordinates, and CNC processing of the core in accordance with the 3D model in a first CNC processing method.

Abstract: Using this method, a coating (1) is manufactured on a substrate (2), which forms a surface of a base body. In this method a layer (3) with ceramic coating material is applied to the substrate in a process chamber (6) using a plasma beam (30) and using an LPPS or LPPS-TF process. The substrate contains at least one metal Me. At a set reaction temperature of the substrate and in the presence of oxygen, an oxide, which results reactively with metal M diffused on the surface, is generated as a ceramic intermediate layer (4). The ceramic layer (3) is deposited on this intermediate layer.

Abstract: A method for the coating of a base body is proposed, in which a layer of a platinum modified aluminide of the kind PtMAl is produced on the base body wherein M designates the metals iron (Fe) or nickel (Ni) or cobalt (Co) or combinations of these metals, wherein the layer is produced by means of a physical deposition out of the gas phase (PVD), wherein at least the two components aluminium (Al) and metal M are physically deposited out of the vapour phase, with the deposition being carried out at a process pressure of at least 0.1 mbar, preferably of at least 0.4 mbar and especially between 0.4 mbar and 0.6 mbar. A workpiece is further proposed, in particular a turbine blade, with a base body on which a layer is applied which is produced using a method of this kind.

Abstract: The invention relates to a component and also an associated coating apparatus and method, including a base body (1), in particular a metallic base body, which includes at least one nickel and/or cobalt base alloy, and also a layer system arranged directly on the base body (1). The layer system includes a bond promoting layer (2) and also a thermally insulating layer arranged on the bond promoting layer, including a TGO layer (3), in particular a slow growing aluminium oxide layer (4) and/or chrome oxide layer as well as at least one oxide ceramic layer which is arranged directly on the TGO layer and a cover layer (5) of an A2E2O7 pyrochlorine arranged on the oxide ceramic layer (4). A preferably includes a lanthanide, in particular gadolinium and E preferably includes zirconium, and also in particular lanthanum zirconate, and/or a perovskite phase.

Abstract: A method is proposed for coating a base body which has at lest one inner passage (101, 102), in which method the coating takes place by means of chemical deposition from the vapour phase, with the base body (10) being arranged on a holding device (3) in a reaction space (21) of a reactor vessel (2) with a process gas being delivered from an external source (7), the process gas being added to an internal generator (4) in the reaction container (2), in which the reactivity of the process gas is increased with the aid of a reactivity changing material and the process gas is conveyed out of the internal generator (4) into the reaction space (21). The process gas is sucked out of the reaction space (21) through the at least one inner passage (101, 102) and through the holding device (3) to an outlet (5) of the reactor vessel (2). Further an apparatus suitable for the method is proposed.

Abstract: Using this method, a coating (1) is manufactured on a substrate (2), which forms a surface of a base body. In this method a layer (3) with ceramic coating material is applied to the substrate in a process chamber (6) using a plasma beam (30) and using an LPPS or LPPS-TF process. The substrate contains at least one metal Me. At a set reaction temperature of the substrate and in the presence of oxygen an oxide, which results reactively with metal M diffused on the surface, is generated as a ceramic intermediate layer (4). The ceramic layer (3) is deposited on this intermediate layer.

Abstract: A target for a sputtering source can be subdivided into a plurality of exchangeable target segments (9). Each target segment (9) contains coating material, wherein each target segment (9) borders on at least two adjacent target segments (9?, 9?), wherein each target segment is connectable to a base body (2, 13, 15) by means of at most one securing means (7, 8, 10).

Abstract: An apparatus for the attachment of a target or target segment (9) of a coating source includes a target or target segment (9) and a target holder (1) which includes a cooling body (3) and connecting means (6,7,8,11) for the attachment of the target or target segment to the cooling body. The connecting means include (3,6,7,8,10,11) electrically and/or thermally conductive means, so that the power supply takes place in a uniform distribution across the target or target segment, and also the heat arising at the target or target segment during the coating method can be uniformly conducted away into the cooling body, by which means more power can be coupled into the coating source and the coating rate is raised.

Abstract: A device operable in a temperature environment in excess of about 1000° C. is provided. The device comprises a substrate and a ceramic thermal barrier layer deposited on at least a portion of the substrate. The layer is formed with a ternary or pseudoternary oxide having a pyrochlore or perovskite structure and a fugative material and having pores or other voluminous defects. The thermal barrier layer advantageously is abradable.

Abstract: A method of placing a ceramic coating on an article of manufacture comprising a substrate formed of a nickel or cobalt-based superalloy, which includes the steps of placing a bonding layer on the substrate and placing an anchoring layer, which is chemically different from the bonding layer and comprises a nitride compound, on the bonding layer. The method further includes the step of placing the ceramic coating on the anchoring layer.

Abstract: The invention relates to a product (1), particularly a gas turbine blade that can be exposed to a hot aggressive gas (7). The product (1) has a metallic basic body (2), which is provided with a thermal barrier coating (4) having a spinel of the composition AB2O4.

Abstract: An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.

Abstract: A method of placing a ceramic coating on an article of manufacture comprising a substrate formed of a nickel or cobalt-based superalloy, which includes the steps of placing a bonding layer on the substrate and placing an anchoring layer, which is chemically different from the bonding layer and comprises a nitride compound, on the bonding layer. The method further includes the step of placing the ceramic coating on the anchoring layer.

Abstract: In order to form a novel article of manufacture, a nickel or cobalt-based superalloy substrate is covered with a protective system resistant to thermal, corrosive and erosive attack. A bonding layer is disposed on the substrate and an anchoring layer on the bonding layer. The anchoring layer is formed as a nitride compound. The nitride compound is aluminum nitride in particular. A ceramic coating is disposed on the anchoring layer. The anchoring layer prevents transmission of diffusion active elements through the anchoring layer to the thermal barrier layer, reduces oxidation of layers therebelow and provides for good heat transmission therethrough.

Abstract: The invention relates to a product (1) designed for hot gas admission with a coating (3) in which chromium nitride (6) is inserted as a diffusion barrier to improve the long-term stability of the coating (3). The invention furthermore relates to a process for producing a coating (3) for a product designed for hot gas admission (1).

Abstract: A device operable in a temperature environment in excess of about 1000° C. is provided. The device comprises a substrate and a ceramic thermal barrier layer deposited on at least a portion of the substrate. The layer is formed with a ternary or pseudoternary oxide having a pyrochlore or perovskite structure and a fugative material and having pores or other voluminous defects. The thermal barrier layer advantageously is abradable.

Abstract: An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.

Abstract: An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.

Abstract: An article that is particularly well suited for use as a gas turbine engine component has a ceramic thermal insulation layer overlaying a bonding layer. The bonding layer is an alloy comprising iron, cobalt and/or nickel and either: the following group 1 elements (by weight percent): Chromium: 3% to 50% Aluminum: 3% to 20% Yttrium and/or a rare-earth element: 0.01% to 0.5% Lanthanum: 0.1% to 10% Hafnium: 0 to 10% Magnesium: 0 to 10% Silicon: 0 to 2%, or the following group 2 elements (by weight percent): Chromium: 3% to 50% Aluminum: 3% to 20% Yttrium and/or a rare-earth element: 0 to 0.5% Lanthanum: 0.1% to 10% Hafnium: 0.1% to 10% Magnesium: 0 to 10% Silicon: 0 to 2%.