The welding can be carried out only after the partial removal of a necessary aluminized portion prior to welding an aluminized component.

A component for a gas turbine engine, the component according to one disclosed non-limiting embodiment of the present disclosure includes an additively manufactured wear surface.

A method of repairing a component of a gas turbine engine in situ, wherein the component includes a deposit, includes directing a flow of gas, which may be an oxygen-containing gas, to the deposit of the component; and heating the component including the deposit while the component is installed in the gas turbine engine and for a duration sufficient to substantially remove the deposit.

Methods and systems for characterizing holes in a combustor liner of a gas turbine engine, and associated repair methods are provided. One method comprises receiving first measured data of the combustor liner in an uncoated state. The method includes determining a first location and a first orientation of a first hole and a first location and a first orientation of a second hole in the combustor liner using the first measured data. The method includes receiving second measured data of the combustor liner in a coated state where the second hole is at least partially obstructed by a coating and the first hole is substantially unobstructed by the coating. The method includes inferring a second location of the second hole of the combustor liner in the coated state using a known spacing between the first location of the first hole and the first location of the second hole. The characterization of the holes may be used to re-drill the obstructed second hole.

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 member attachment support system is for supporting work of attaching a plurality of members to a device. The member attachment support system includes: an identification information storage unit provided for each of the plurality of members and configured to store identification information associated with an attachment position of each of the plurality of members; a terminal device configured to acquire the identification information from the identification information storage unit; and a display device configured to display a support image that indicates the attachment position corresponding to the identification information acquired by the terminal device.

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.

Additively manufactured thrust chambers and thrust chambers with integral fluid manifolds, and hybrid additive manufacturing methods for their production, are provided. Hybrid additive manufacturing techniques may combine a variety of processes including, WAAM, PBF, cold spray and DED, for example, to produce objects with variant dimensional requirements, i.e., large overall size and small features. Hybrid additive manufacturing may be defined as provide various process layers within any manufactured object. These process layers in turn allow for the introduction of variable feature and size distribution throughout the manufactured object. Hybrid process layers according to aspects may also allow the use of a variety of materials or may use a single material across the various process layers.

In this assembly method for assembling a bulkhead to an outer liner by fitting the bulkhead into the outer liner in a prescribed position, the bulkhead having a plurality of through-holes formed in a circumferential direction, with an axis as a central axis, and the outer liner having a plurality of through-holes formed in a circumferential direction, with an axis as a central axis, a computer executes: a size detection step for detecting a size of an overlapping region between each corresponding through-hole and through-hole, with the bulkhead fitted into the outer liner; and an overlapping region identification step for identifying, on the basis of the sizes of all the overlapping regions, overlapping regions in which a positional relationship between the through-hole and the through-hole requires adjustment.