Abstract: Martensitic steel with Z phase, powder, and blank or component—alloy, at least including (in % by weight): carbon (C): 0.16%-0.24%, silicon (Si): 0.0%-0.08%, manganese (Mn): 0.04%-0.16% chromium (Cr): 10.6%-11.5%, molybdenum (Mo): 0.5%-0.9%, tungsten (W): 2.2%-2.6%, cobalt (Co): 3.0%-3.6%, nickel (Ni): 0.09%-0.19%, boron (B): 0.0035%-0.01%, nitrogen (N): 0.001%-0.025%, titanium (Ti): 0.01%-0.04%, copper (Cu): 1.20%-2.30%, optionally vanadium (V): 0.10%-0.30%, niobium (Nb): 0.02%-0.08%, aluminium (Al): 0.003%-0.06%, balance: iron (Fe).

Abstract: An alloy which includes at least the following (in % by weight): carbon (C): 0.15%-0.25%; silicon (Si): 0.0%-0.08%; manganese (Mn): 0.03%-0.20%; chromium (Cr): 9.5%-10.5%; molybdenum (Mo): 0.4%-1.0%; tungsten (W): 1.6%-2.4%; cobalt (Co): 2.5%-3.5%; nickel (Ni): 0.0%-0.40%; boron (B): 0.003%-0.02%; nitrogen (N): 0.0%-0.40%; titanium (Ti): 0.02%-0.10%; vanadium (V): 0.10%-0.30%; niobium (Nb): 0.02%-0.08%; copper (Cu): 1.20%-2.10%; and aluminum (Al): 0.003%-0.06%, in particular 0.005%-0.04%; the remainder being iron (Fe).

Abstract: The use of especially an aluminum alloy on a metal substrate in a PVD-AlTiN coating results in good corrosion and erosion protection.

Abstract: A layer system having a metallic substrate, in particular made of a >=9% by weight chromium steel, in particular with roughness of the substrate <=2 ?m and optionally an intervening chromium layer directly on the substrate, in particular made of Cr/CrN, an underlayer or middle layer of AlCr, and an outer layer, in particular outermost layer, of AlCrO, where the AlCr and AlCrO layers in particular are PVD coatings wherein a shark skin effect is achieved with a simple geometric arrangement, and can be used particularly for compressor blades.

Abstract: An alloy which includes at least the following (in % by weight): carbon (C): 0.15%-0.25%; silicon (Si): 0.0%-0.08%; manganese (Mn): 0.03%-0.20%; chromium (Cr): 9.5%-10.5%; molybdenum (Mo): 0.4%-1.0%; tungsten (W): 1.6%-2.4%; cobalt (Co): 2.5%-3.5%; nickel (Ni): 0.0%-0.40%; boron (B): 0.003%-0.02%; nitrogen (N): 0.0%-0.40%; titanium (Ti): 0.02%-0.10%; vanadium (V): 0.10%-0.30%; niobium (Nb): 0.02%-0.08%; copper (Cu): 1.20%-2.10%; and aluminum (Al): 0.003%-0.06%, in particular 0.005%-0.04%; the remainder being iron (Fe).

Abstract: Provided is a coating system for a substrate, the system including a first, second and third layer. In the system, the first layer is designed as an adhesion promoter layer, the second layer is a ductile metal layer with a columnar structure and the uppermost, third layer is a ceramic oxide layer with a high hardness value. The substrate is ideally an element of a compressor component of a stationary gas turbine. Also disclosed is a method for producing the coating system.

Abstract: The use of especially an aluminum alloy on a metal substrate in a PVD-AlTiN coating results in good corrosion and erosion protection.

Abstract: A compressor blade for a gas turbine is provided. The compressor blade has a blade substrate that consists of a metal alloy and has an aluminum diffusion zone on a surface of the blade substrate. In addition, the compressor blade has a hard material coating provided on the surface of the blade substrate. A compressor that has a compressor blade and a method of producing such a compressor blade is also provided.

Abstract: An iron-based steel comprising at least (in wt. %): carbon (C): 0.01%-0.10%; silicon (Si): 0.02%-0.7%; manganese (Mn): 0.3%-1.0%; chromium (Cr): 8.0%-10%; molybdenum (Mo): 0.1%-1.8%; cobalt (Co): 0.8%-2.0%; nickel (Ni): 0.008% -0.20%; boron (B): 0.004% -0.01%; nitrogen (N): 0.03% -0.06%; vanadium (V): 0.1% -0.3%, particularly 0.15% -0.022% of vanadium (V), more particularly 0.185% of vanadium (V); niobium (Nb): 0.01% -0.07%; optionally tungsten (W): 2.0% -2.8%, particularly 2.4% of tungsten; the remainder being iron (Fe); wherein said steel consists in particular of these elements.

Abstract: A steel having the following composition: carbon: 0.08%-0.12%, preferably 0.10%; silicon: 0.04%-0.08%; manganese: 0.08%-0.012%; chromium: 9%-II%; molybdenum: 0.4%-1.0%; tungsten: 1.6%-2.4%; cobalt: 2.5%-3.5%; nickel: 0.10%-0.24%; boron: 0.006%-0.01%; nitrogen: 0.002%-0.01%; titanium: 0.008%-0.03%; vanadium: 0.015%-0.029%; niobium: 0.03%-0.07%; optionally copper: 1.00%-2.5%; aluminum: 0.04%-0.10%; the remainder being iron, wherein said steel has improved properties, since no further Z-phase formation occurs.

Abstract: A method for producing a component for a turbomachine, having the additive build-up of the component by an additive production method from a base material for the component and the introduction of material fibers into a construction for the component during the additive build-up in such a way that the material fibers are oriented in a circumferential direction of the component around a component axis and in such a way that a fiber composite material is produced, including the material fibers and a base material that is solidified by the additive build-up. A corresponding component is produced by the method and a corresponding device is used for producing the component.

Abstract: Provided is a coating system for a substrate, the system including a first, second and third layer. In the system, the first layer is designed as an adhesion promoter layer, the second layer is a ductile metal layer with a columnar structure and the uppermost, third layer is a ceramic oxide layer with a high hardness value. The substrate is ideally an element of a compressor component of a stationary gas turbine. Also disclosed is a method for producing the coating system.

Abstract: After remelting in a suitable mold for reducing grain boundaries, an oxidation-resistant material is epitaxially grown so that the oxidation resistance of a repaired material or also of a new part is improved.

Abstract: A compressor blade for a gas turbine is provided. The compressor blade has a blade substrate that consists of a metal alloy and has an aluminum diffusion zone on a surface of the blade substrate. In addition, the compressor blade has a hard material coating provided on the surface of the blade substrate. A compressor that has a compressor blade and a method of producing such a compressor blade is also provided.

Abstract: A turbine blade or vane having a thermal barrier coating, the thermal barrier coating including an inner layer and an outer layer, which is arranged directly or indirectly on the inner layer, wherein the inner layer has flow ducts which are connected fluidically to one another and which are connected to a cooling fluid supply duct. The outer layer has flow ducts which are connected fluidically to one another and which are connected to a cooling fluid supply duct.