The invention relates to a method for producing a rotor of a flow engine, namely an integrally bladed rotor with an integral outer shroud, comprising at least the following steps: a rotor blank comprising the integral rotor blades and the integral outer shroud is first produced by means of a generative production method; the rotor blank is then subjected to a separating surface treatment at flow-guiding sections and is subjected, separately therefrom, to a machining surface treatment at non-flow-guiding sections.

A gas turbine part with a cooling hole, is fabricated by first forming a model of a wall of a gas turbine part. The wall is defined by first and second surfaces, the first surface having an aperture indentation possessing a complex geometry and extending into but not all the way through the wall of the gas turbine part. A mold of the wall of the gas turbine part is formed using the model and is used to cast the wall of the gas turbine part by lost-material casting. A passage is drilled through the resulting casting. This passage extends from the aperture indentation in the first surface through to the second surface.

A method of manufacturing an airfoil includes creating a plurality of cavities separated by a plurality of internal ribs in an airfoil forging. At least one hole is drilled in at least one of the plurality of internal ribs with a laser drilling tool. At least one hole extends perpendicularly to a wall of the rib.

A forming system includes a femtosecond laser and a control unit that includes one or more processors operatively connected to the femtosecond laser. The femtosecond laser is configured to emit laser pulses onto an inner surface of a face sheet of an acoustic inner barrel. The acoustic inner barrel includes an acoustic core comprising an array of hexagonal cells attached to an outer surface of the face sheet that is opposite the inner surface. The control unit is configured to control the femtosecond laser to laser drill a plurality of perforations in the face sheet via emitting laser pulses at pulse durations between about 100 femtoseconds and about 10,000 femtoseconds and at frequencies over 100,000 Hz such that the perforations are formed without burning portions of the face sheet or the acoustic core surrounding the perforations.

Various embodiments include a system for machining a hole in a turbine blade. The system can include: a mount for engaging a first side of a turbine rotor, the mount including: a drill plate for coupling with the first side of the turbine rotor, the drill plate having: a body; a feed opening on a first side of the body; a passage extending from the feed opening through the body; and a second opening on a second side of the body, the second opening coupled with the passage and positioned to align with the pre-formed hole in the turbine rotor; an alignment bushing for engaging the pre-formed hole in the rotor at a second side of the rotor; and a cutting device for extending through the body and alignment bushing, the cutting device for machining the hole in the blade, the cutting device aligned along a chamfer axis relative to a primary axis of the turbine rotor.

A method for manufacturing a solid propellant includes: forming a tool of layers of a first material wherein cuts in the layers form a first interior chamber in the tool; using the tool to mold a second material in the first interior chamber; removing the molded second material from the tool; using the molded second material to mold an interior chamber in a rocket propellant grain; and removing the molded second material from the rocket propellant grain.

An apparatus and method regarding forming a cooling hole in a component for a turbine engine, with the component held in a hole-forming machine with a laser carried on a multi-axis carriage and defining an optical path, the method comprising forming a set of cooling holes in the component with a laser mounted to the multi-axis carriage, estimating a total airflow through the set of cooling holes based on a set of data regarding the flow effectiveness of the set of cooling holes, and forming a second set of cooling holes with the laser.

The disclosure describes an article and a method of making the same that includes a substrate defining an outer surface, a bond coat on the outer surface of the substrate, the bond coat defining a textured surface having a plurality of cells, each cell having a geometry and a depth, where the depth of a respective cell is different than the depth of at least one adjacent cell, and a coating formed on the textured surface of the bond coat.

A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein is provided. The plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: TVA, TVB, TVC, TVD and TVE of Table 1.

A method of preventing spallation for a geometrically segmented thermally insulating top coat on an article, the method comprising forming a surface feature in a surface of the article; forming a crack deflection feature in the surface proximate the surface feature; disposing the thermally insulating topcoat over the surface feature; and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the surface feature.