Disclosed is a method for the heat treatment of at least one bar made from titanium aluminide alloy for manufacturing at least one low-pressure turbine blade for a turbomachine, comprising hot isostatic pressing of the bar, characterised in that the hot isostatic pressing (121) is followed, after a temperature transition phase, by a step of heat treatment (122) of the bar at a temperature in the immediate vicinity of the eutectoid temperature of the alloy, the temperature being suitable for the formation of an alloy microstructure with a volume fraction of at least 90% single-phase grains γ and a volume fraction of at most 10% of lamellar grains α+γ, the step being followed by a controlled cooling step (123).

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.

A method of manufacturing a TiAl alloy impeller includes a blank preparation step in which a blank of the TiAl alloy impeller is prepared, wherein the blank has a shaft portion and a plurality of blades, and a thickness of an outer edge of each of the blades of the blank is set so as to be larger than a thickness of an outer edge of a blade of the TiAl alloy impeller, and an additional work step in which an additional work is performed on each of the blades of the blank. In the additional work step, the additional work is performed on a first surface of a portion that includes at least the outer edge of each of the blades or the first surface and a second surface of the portion thereof.

A method of manufacturing a TiAl alloy impeller includes a blank preparation step in which a blank of the TiAl alloy impeller is prepared, wherein the blank has a shaft portion and a plurality of blades, and a thickness of an outer edge of each of the blades of the blank is set so as to be larger than a thickness of an outer edge of a blade of the TiAl alloy impeller, and an additional work step in which an additional work is performed on each of the blades of the blank. In the additional work step, the additional work is performed on a first surface of a portion that includes at least the outer edge of each of the blades or the first surface and a second surface of the portion thereof.

A method for manufacturing a propeller for a propeller pump includes providing a base propeller including a hub extending from an axial end in the axial direction, and a plurality of blades fixedly connected to the hub, each blade including a pressure side, a suction side, a leading edge, an initial trailing edge, and a blade tip extending from the leading edge to the initial trailing edge at the end of the blade facing away from the hub, trimming each of the blades of the base propeller the axial direction, and forming a modified trailing edge bye removing a part of the initial trailing edge along the entire pressure side from the hub to the blade tip.

Tube forming methods can be used for efficient transition in the production of tubes having varying thickness. Material used to form consecutive tubes may have the same thickness along a separation plane separating a first discrete section from a second discrete section of the material, and the first discrete section and the second discrete section may each have varying thickness in a feed direction of the material. With such a thickness profile, the first discrete section of the material may be formed into a first cylinder having varying thickness and separated from the second discrete portion as the second discrete section is formed into a second cylinder having varying thickness. In particular, the transition between the first cylinder and the second cylinder may be achieved without scrap and/or interruption, resulting in cost-savings and improvements in production throughput associated with forming tubes having varying thickness.

Tube forming methods can be used for efficient transition in the production of tubes having varying thickness. Material used to form consecutive tubes may have the same thickness along a separation plane separating a first discrete section from a second discrete section of the material, and the first discrete section and the second discrete section may each have varying thickness in a feed direction of the material. With such a thickness profile, the first discrete section of the material may be formed into a first cylinder having varying thickness and separated from the second discrete portion as the second discrete section is formed into a second cylinder having varying thickness. In particular, the transition between the first cylinder and the second cylinder may be achieved without scrap and/or interruption, resulting in cost-savings and improvements in production throughput associated with forming tubes having varying thickness.

A method for coating a part having a surface that has cooling fluid openings that adjoin cooling fluid ducts inside the part. A device analyzes the surface of a part having a surface that has cooling fluid openings which adjoin cooling fluid ducts inside the part, the device being usable in the aforementioned method. The disclosed device and/or the disclosed method is used during the manufacturing and/or overhauling of parts of a turbomachine.

A method for coating a part having a surface that has cooling fluid openings that adjoin cooling fluid ducts inside the part. A device analyzes the surface of a part having a surface that has cooling fluid openings which adjoin cooling fluid ducts inside the part, the device being usable in the aforementioned method. The disclosed device and/or the disclosed method is used during the manufacturing and/or overhauling of parts of a turbomachine.

The present invention relates to a method for coating a component, wherein the component has a first and a second surface, and wherein the first and the second surface adjoin each other at an edge, in which method i) first of all, the edge between the first and the second surface is rounded, and ii) subsequently, a coating is applied to the first surface.