The invention relates to a method for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating, of a thermal gas turbine. The method according to the invention comprises the steps of removing a blade tip armor plating of the turbine blade at least in the region of the damaged blade tip and producing a repair surface (12), removing only a part of the blade coating of the turbine blade in the region of the repair surface while preserving a part of the blade coating separated from the repair surface (14), restoring the blade tip reinforcement (20), and restoring the blade coating in the region of the repaired blade tip (22). The invention furthermore relates to a device for carrying out such a method.

A combustor which can be manufactured without requiring large-scale equipment and with a small number of processes and has a cooling fluid flow path sealed with high reliability. The combustor includes an inner cylinder made of metal constituting a combustion chamber, a cooling fluid flow path formed on an outer surface of the inner cylinder, and a sealing layer covering the outer surface of the inner cylinder to seal the cooling fluid flow path. The sealing layer is constituted by a bonded body of metal wires wound around the outer surface of the inner cylinder and metallurgically bonded to each other, and the sealing layer is bonded to the outer surface of the inner cylinder by metallurgical bonding.

A turbine wheel consists of a first shroud component and a second bladed disc component. The shroud component comprises a shroud structure, a hub structure and a spoke formed integrally therewith and extending between the shroud structure and the hub structure. The bladed disc component comprises a hub member having inner and outer rims, turbine blades disposed on the outer rim, and at least one receiving zone for receiving the spoke, said at least one receiving zone extending radially between the inner and outer rims. The shroud component and the bladed disc component are connected and thus provide the turbine wheel with a shrouded portion. A shrouded turbine wheel can therefore be conveniently assembled starting from at least two components. Further, these components have simplified geometries for easy manufacture, for example using a casting technique, while the overall mechanical performance of the turbine is preserved or improved.

A method for repairing a component is provided, including the following steps: introducing a recess into the component, via which recess a damaged region in the component is removed; positioning a filler body in the recess; and fixedly, i.e. non-detachably, connecting the filler body to the component, wherein the filler body is provisionally secured to the component prior to establishing the fixed connection to the component, in that a securing element is placed over the filler body and the securing element is attached to the component, wherein the securing element is removed again after the establishing of the fixed connection between the filler body and the component.

A rotor for at least one of a turbine and a compressor of a supercharging device may include a shaft defining an axis of rotation and at least one impeller. The at least one impeller may have a thread which is arranged coaxially to the axis of rotation. The shaft may include a complementary thread which is arranged coaxially to the axis of rotation. The shaft and the at least one impeller may be secured together via the respective threads. The shaft and the at least one impeller may be fixed with respect to one another via at least one of a soldered connection, a welded connection, an adhesive bond, a clamped connection and a crystallization connection.

The invention relates to a method for producing a mistuning component. The method comprises the following steps: a) producing a container (34) having at least one chamber (36); b) producing a lid (32, 32′); c) inserting at least one impulse element into the chamber (36); d) joining the lid (32, 32′) and the container (36), wherein joining is carried out by soldering/brazing.

A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.

Combining a precipitation-hardening nickel-base alloy with a steel or titanium substrate makes it very easy to repair parts, the nickel-base alloy having good erosion-resistant properties. A method for producing is disclosed. In particular for repairing, a component having a substrate, in particular turbine blades made of steel or titanium, in particular made of martensitic or precipitation-hardening chromium-rich steels, with a localized deposition weld or with an affixed shaped part, in which a precipitation-hardening nickel-based alloy is used as the localized deposition weld or as the shaped part, in which a laser powder deposition weld or an arc deposition weld is performed.

A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.

A guide vane for a turbomachine, having a blade airfoil and at least one platform, to which the blade airfoil is connected. A cooling channel system is provided for cooling the platform and the blade airfoil. The platform has, on the side thereof facing the airfoil, at least one sealing lip for sealing to a rotating system of the turbomachine. At least one cooling channel extends through the sealing lip, which cooling channel forms part of the cooling channel system.