Abstract: The present invention relates to a component of a turbomachine with a repair layer and a method for repairing wear-damaged components (1, 10) of a turbomachine, in particular of elements of a flow duct boundary, having the following method steps: preparing the area to be repaired, in order to provide a smooth and clean surface (4), applying an Ni-based braze (7) with a proportion of hard material particles (8) to the surface (4) to form a repair layer (15), wherein the hard material particles comprise hard alloys based on cobalt or nickel, heat treating the component to braze the repair layer onto the component under vacuum conditions.

Abstract: A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material.

Abstract: The present invention relates to a component of a turbomachine with a repair layer and a method for repairing wear-damaged components (1, 10) of a turbomachine, in particular of elements of a flow duct boundary, having the following method steps: preparing the area to be repaired, in order to provide a smooth and clean surface (4), applying an Ni-based braze (7) with a proportion of hard material particles (8) to the surface (4) to form a repair layer (15), wherein the hard material particles comprise hard alloys based on cobalt or nickel, heat treating the component to braze the repair layer onto the component under vacuum conditions.

Abstract: Disclosed is a process for producing a wear-resistant layer, in particular on components of gas turbines or aero engines. The process comprises providing a component with a titanium material on at least part of a surface on which the wear-resistant layer is to be produced, applying a solder formed from a cobalt base material to the titanium material, soldering the solder to the titanium material by applying heat and producing at least one diffusion zone between solder and titanium material which comprises intermetallic phases.

Abstract: A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.

Abstract: Disclosed is a process for producing a wear-resistant layer, in particular on components of gas turbines or aero engines. The process comprises providing a component with a titanium material on at least part of a surface on which the wear-resistant layer is to be produced, applying a solder formed from a cobalt base material to the titanium material, soldering the solder to the titanium material by applying heat and producing at least one diffusion zone between solder and titanium material which comprises intermetallic phases.

Abstract: A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.

Abstract: A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material.

Abstract: A method for repairing a component of a gas turbine and a solder alloy are disclosed. In an embodiment, the method includes applying the solder alloy to the component in an area of the component having a punctiform damage or a linear imperfection, where the solder alloy is a mixture of a NiCoCrAlY alloy and a Ni-based solder. A molded repair part made of the solder alloy is applied to the component in an area of the component having a planar defect. The component is heat treated to solder the molded repair part on the component and to solder the solder alloy applied to the component in the area of the component having the punctiform damage or the linear imperfection. The component is cooled after the heat treating and, following the cooling, the component is further heat treated.

Abstract: A method for repairing a component of a gas turbine and a solder alloy are disclosed. In an embodiment, the method includes applying the solder alloy to the component in an area of the component having a punctiform damage or a linear imperfection, where the solder alloy is a mixture of a NiCoCrAlY alloy and a Ni-based solder. A molded repair part made of the solder alloy is applied to the component in an area of the component having a planar defect. The component is heat treated to solder the molded repair part on the component and to solder the solder alloy applied to the component in the area of the component having the punctiform damage or the linear imperfection. The component is cooled after the heat treating and, following the cooling, the component is further heat treated.

Abstract: A method for producing a blade tip armor plating on a blade of a turbomachine, in particular on a high-pressure compressor rotary blade of a gas turbine, having the following steps: a) provision of a blade made of a nickel base material; b) application of a solder to a blade tip of the blade, the solder being a nickel base solder; c) application of hard material particles of cubic boron nitride to the solder, the hard material particles of cubic boron nitride being coated with titanium or with a titanium base material; d) fusion of the solder in a vacuum in order to form a matrix that at least partially surrounds the hard material particles; and e) fixing of the blade tip armor plating through cooling.

Abstract: The invention concerns a medical tool, in particular a vertebral distractor (1), with a first (2) and a second link part (3), wherein the first link part (2) is connected with the second link part (3) via a rotation axis (4), and therein a grip element (6,8) and a pliers element (5,7) is provided on each link part (2,3), which are operatively associated with each other, and wherein the two grip elements (6,8) are provided on a first side relative to the rotation axis (4) and the two pliers elements (5,7) are provided on a second side lying opposite to the first side, and wherein a valve (12) is seatable in the area of the free axial ends of a pliers element (5,7) and releaseably connected by a securing mechanism of the first type, and wherein a push button of the first type (14) is provided on the securing mechanism of the first type.

Abstract: A medical instrument includes a handle having metal cores which are connected with an elongated base or lower member and an elongated upper or movable member. A spring is connected with the metal cores and urges the metal cores toward an initial relationship. Silicone rubber coverings are provided over the metal cores. The silicone rubber covers provide a soft grip which is comfortable for a user of the medical instrument, does not become slippery in an operating environment, and can be cleaned by steam sterilization.

Abstract: The invention concerns medical tool, in particular a vertebral distractor (1), with a first (2) and a second link part (3), wherein the first link part (2) is connected with the second link part (3) via a rotation axis (4), and therein a grip element (6,8) and a pliers element (5,7) is provided on each link part (2,3), which are operatively associated with each other, and wherein the two grip elements (6,8) are provided on a first side relative to the rotation axis (4) and the two pliers elements (5,7) are provided on a second side lying opposite to the first side, and wherein a valve (12) is seatable in the area of the free axial ends of a pliers element (5,7) and releaseably connected by means of a securing mechanism of the first type, and wherein a push button of the first type (14) is provided on the securing mechanism of the first type, by means of which the connection can be released.