Abstract: A method and a turbine part having a coating with a matrix layer that includes a high temperature resistant hydrophobic polysiloxane filler, wherein the coating has superior mechanical strength and temperature resistance.

Abstract: The invention relates to a device for High Velocity Oxygen Fuel thermal spraying process for coating a component, especially a gas turbine component. The device includes a liquid fuel fired combustion chamber, a de-Laval section, a powder injector block with powder injectors and a barrel all arranged around and along an axis. The powder injector block includes at least four powder injectors arranged in an equal circumferential distance around the axis and an exchangeable hot gas section insert inside the powder injector block designed as a cylindrical bush with at least four openings, the openings being arranged in an equal circumferential distance around the axis in the cylinder, wherein the bush is fixed by the at least four powder injectors extending through said openings.

Abstract: A method for reconditioning a hot gas path part of a gas turbine to flexibly adapt an operation regime of said gas turbine for subsequent operation intervals. The method includes providing a hot gas path part to be reconditioned; removing a predetermined area of the hot gas path part, resulting in a cutout at the hot gas path part; and manufacturing a coupon for insertion into the cutout to replace the removed area of the hot gas path part. The method further includes inserting the coupon into the cutout; and joining the hot gas path part with the coupon. The coupon is manufactured by a selective laser melting method resulting in a fine grain sized material with significantly improved low cycle fatigue lifetime. The hot gas path part is coated, at least in an area including the inserted coupon, with a metallic overlay with improved thermo-mechanical fatigue and oxidation lifetime.

Abstract: The invention relates to a coating system for a component of a turbomachine, which includes at least two different base powders. Each of the at least two different base powders has an individual predetermined distribution within the coating system. Further, each of the at least two different base powders is responsible for a specific property of the coating system.

Abstract: The invention relates to a device for High Velocity Oxygen Fuel thermal spraying process for coating a component, especially a gas turbine component. The device includes a liquid fuel fired combustion chamber, a de-Laval section, a powder injector block with powder injectors and a barrel all arranged around and along an axis. The powder injector block includes at least four powder injectors arranged in an equal circumferential distance around the axis and an exchangeable hot gas section insert inside the powder injector block designed as a cylindrical bush with at least four openings, the openings being arranged in an equal circumferential distance around the axis in the cylinder, wherein the bush is fixed by the at least four powder injectors extending through said openings.

Abstract: A method and a turbine part having a coating with a matrix layer that includes a high temperature resistant hydrophobic polysiloxane filler, wherein the coating has superior mechanical strength and temperature resistance.

Abstract: A method for reconditioning a hot gas path part of a gas turbine in order to flexibly adapt an operation regime of said gas turbine for subsequent operation intervals is disclosed. The method includes providing a hot gas path part to be reconditioned; removing a predetermined area of said hot gas path part, resulting in a cutout at said hot gas path part; and manufacturing a coupon for being inserted into said cutout to replace said removed area of said hot gas path part. The method further includes inserting said coupon into said cutout; and joining said hot gas path part with said inserted coupon. The coupon is manufactured by a selective laser melting (SLM) method resulting in a fine grain sized material with significantly improved low cycle fatigue (LCF) lifetime. The hot gas path part is coated, at least in an area comprising said inserted coupon, with a metallic overlay with improved thermo-mechanical fatigue (TMF) and oxidation lifetime.

Abstract: The invention proposes a method for applying a high-temperature stable coating layer on the surface of a component, which includes: providing a component with a surface to be coated; providing a powder material containing at least a fraction of sub-micron powder particles; and applying said powder material to the surface of the component by means of a spraying technique to build up a coating layer, whereby said sub-micron powder particles are each at least partially surrounded by an oxide shell and establish with their oxide shells an at least partially interconnected sub-micron oxide network within said coating layer.

Abstract: The invention relates to a coating system for a component of a turbomachine, which includes at least two different base powders. Each of the at least two different base powders has an individual predetermined distribution within the coating system. Further, each of the at least two different base powders is responsible for a specific property of the coating system.

Abstract: An abradable coating system (2-8) for a turbine or a compressor is proposed has at least one layer of woven or non-woven tissue (15) or foam made of: ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof. A free-standing preformed element (18) has at least one layer of such a woven or non-woven tissue or foam is filled with fillers and/or binder. A method prepares such a system. Finally, a method for the repair of an abradable coating portion of a turbine or the compressor component (9) includes in a first optional step that the damaged portion is at least partly removed and/or cleaned and/or surface treated, and in a second step at least one free-standing preformed abradable coating element (18) or a complete abradable coating system is attached to the component (9), preferably by using a matrix, wherein for example only a center part (2) or a fraction of a center part (2) is replaced.

Abstract: A method and a turbine part having a coating with a matrix layer that includes a high temperature resistant hydrophobic polysiloxane filler, wherein the coating has superior mechanical strength and temperature resistance.

Abstract: An abradable coating system (2-8) for a turbine or a compressor is proposed has at least one layer of woven or non-woven tissue (15) or foam made of: ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof. A free-standing preformed element (18) has at least one layer of such a woven or non-woven tissue or foam is filled with fillers and/or binder. A method prepares such a system. Finally, a method for the repair of an abradable coating portion of a turbine or the compressor component (9) includes in a first optional step that the damaged portion is at least partly removed and/or cleaned and/or surface treated, and in a second step at least one free-standing preformed abradable coating element (18) or a complete abradable coating system is attached to the component (9), preferably by using a matrix, wherein for example only a center part (2) or a fraction of a center part (2) is replaced.