A method and an apparatus for collecting powder samples in real-time in powder bed fusion additive manufacturing may involves an ingester system for in-process collection and characterizations of powder samples. The collection may be performed periodically and uses the results of characterizations for adjustments in the powder bed fusion process. The ingester system of the present disclosure is capable of packaging powder samples collected in real-time into storage containers serving a multitude purposes of audit, process adjustments or actions.

Removal of substrates in a composite substrate is facilitated, and flaking of the composite substrate in an unintended process is prevented. A method for manufacturing a composite substrate includes: forming a first bonding material in a first surface of a first substrate; forming, in the first surface, at least one groove located more inward than a periphery in a plan view of the first substrate; forming the first bonding material along an inner wall of the at least one groove, the first bonding material not filling into space enclosed by the inner wall of the at least one groove; forming a second bonding material on a second surface of a second substrate; and bonding the first bonding material and the second bonding material together in a region except the at least one groove.

An airfoil component for attaching to a cropped airfoil is provided. The cropped airfoil comprises a cropped airfoil attachment section and a cropped first side opposite a cropped second side, which each extend axially between a cropped first edge and a cropped second edge to define a cropped chord length. The airfoil component comprises a body having a component first side opposite a component second side. The body defines an attachment section for attaching the airfoil component to the cropped airfoil at the cropped airfoil attachment section. The attachment section extends axially between a component first edge and a component second edge to define a component chord length, and the attachment section is oversized with respect to the cropped airfoil attachment section such that the component chord length is longer than the cropped chord length. Systems and methods also are provided.

A pressure vessel assembly includes a plurality of lobes, each lobe having at least one vertically arranged interior wall, the lobes positioned in a side by side arrangement such that a first interior wall of a first lobe is positioned adjacent a second interior wall of a second lobe, the first interior wall having a first wall top and bottom side, the second interior wall having a second wall top and bottom side, the first wall top side joined to the second wall top side and the first wall bottom side joined to the second wall bottom side. Also included are first and second end wall surfaces of each of the plurality of lobes. Further included is a plurality of end caps, each of the end caps joined to the end wall surfaces of the lobes, each of the end caps joined to at least one adjacent end cap.

A method and an apparatus of a powder bed fusion additive manufacturing system that enables a quick change in the optical beam delivery size and intensity across locations of a print surface for different powdered materials while ensuring high availability of the system. A dynamic optical assembly containing a set of lens assemblies of different magnification ratios and a mechanical assembly may change the magnification ratios as needed. The dynamic optical assembly may include a transitional and rotational position control of the optics to minimize variations of the optical beam sizes across the print surface.

A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

A method of fabricating plates of super-hard material and cutting techniques suitable for such a method. A method of fabricating a plate (14) of super-hard material, the method comprising: • providing a substrate (4) have a lateral dimension of at least 40 mm; • growing a layer of super-hard material on the substrate (4) using a chemical vapour deposition process; and • slicing one or more plates (14) of super-hard material from the substrate using a collimated cutting beam (8), the or each plate of super-hard material (14) having a lateral dimension of at least 40 mm, wherein the collimated cutting beam (8) is collimated with a half angle divergence of no more than 5 degrees.

A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

A method is provided for manufacturing a segment of a drill string, such as a tubular tool, from a plurality of layers. The method includes arranging a plurality of layers based on a selected length of the segment. Each of the plurality of layers includes an aperture that is received over an alignment feature that restricts movement of the plurality of layers to two or fewer degrees of freedom. A joining process is performed to join the plurality of layers, which may include at least one replacement layer.

New alpha-beta titanium alloys are disclosed. The new alloys generally include 7.0-11.0 wt. % Al, and 1.0-4.0 wt. % Mo, wherein Al:Mo, by weight, is from 2.0:1-11.0:1, the balance being titanium, any optional incidental elements, and unavoidable impurities. The new alloys may realize an improved combination of properties as compared to conventional titanium alloys.