Methods for depositing protective coatings on aerospace components are provided and include sequentially exposing the aerospace component to a chromium precursor and a reactant to form a chromium-containing layer on a surface of the aerospace component by an atomic layer deposition process. The chromium-containing layer contains metallic chromium, chromium oxide, chromium nitride, chromium carbide, chromium silicide, or any combination thereof.

A coated gas turbine engine part includes a substrate and a calcium-magnesium-alumino-silicate CMAS protection layer present on the substrate. The layer includes a first phase of a calcium-magnesium-alumino-silicate CMAS protection material and a second phase including particles of an anti-wetting material dispersed in the first phase.

A process for cold working of the inner surface of a bore in a centrifugal compressor wheel along only a fractional portion of the bore length (i.e., along less than a full axial length of the bore), thereby creating a zone of compressive residual hoop stress in the metal surrounding the bore where the wheel needs the beneficial residual stress. The process purposefully avoids cold working of the bore at locations adjacent to high-stress areas and features of the wheel, where cold working in such locations could negatively impact the wheel's overall life.

Provided is a bilateral ultrasonic rolling processing track coordination method for a blade surface, the method comprising: step S1, performing layering processing on a blade to acquire a contour curve of “A”-shaped and “n”-shaped blade edges of a blade model at different heights; step S2: determining the endpoints of a blade processing track; and step S3: planning the thickness and the rotation angle of the blade, comprising: step S31, solving a main direction angle α.sub.main of the contour curve; step S32, solving the thickness d of the blade; step S33, solving a rotation angle required by blade processing when the blade edge is “A”-shaped; and step S34, solving the rotation angle required by blade processing when the blade edge is “n”-shaped. According to the method, blade deformation generated by an ultrasonic rolling force is reduced, the processing efficiency is improved, and the blade processing precision is also improved.

A method includes applying a material coating to a surface of a machine component, wherein the material coating is formed from a combination of a hardfacing material, aluminum-containing particles, and a braze material. The method also includes thermally treating the material coating at a temperature to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material, and the braze material is configured to facilitate binding between the material coating and the surface of the machine component.

A method of forming a gas turbine engine component including an airfoil and at least one shroud includes the steps of (1) machining a gas path surface of the at least one shroud utilizing a non-electrochemical machining (ECM) process, and (2) then utilizing ECM on at least the airfoil.

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and a root section in a spanwise direction. The airfoil section defines pressure and suction sides separated in a thickness direction. A sheath extends in the spanwise direction along at least one of the pressure and suction sides of the airfoil section. A tip cap extends in the chordwise direction along the at least one of the pressure and suction sides. The sheath includes a first set of interface members. The tip cap includes a second set of interface members interleaved with the first set of interface members to establish at least one joint along an external surface of the at least one of the pressure and suction sides. A method of assembly for an airfoil is also disclosed.

A method for optimizing energy conversion installation service measures, wherein the energy conversion installation has at least the following machines: at least one gas turbine; at least one generator; and optionally at least one steam turbine; wherein repairs are carried out on the at least one machine, in particular a defective component or defective components of the at least one machine either is/are or will be replaced by a new, identical component or new, identical components and/or repaired; and wherein, while carrying out these repairs, further measures for extending the service life of machines or the components thereof and/or further measures for optimizing machines or the components thereof are carried out.

A turbomachine blade is made of composite material formed of woven fibers and embedded in a polymerized resin. The blade includes a root connected by a stilt to a vane which comprises a pressure side and a suction side. At least one anti-wear strip of fabric is located on a surface of the root and/or the stilt. At least one anti-wear strip is secured to the root surface in a unitary manner by the resin.

An additively manufactured (AM) object may include a body including an opening in an exterior surface thereof, the opening having a shape and a first area at the exterior surface of the body. A mask may be positioned over the opening. The mask has the shape of the opening and a second area that is larger than the first area so as to overhang the exterior surface of the body about the opening. A plurality of support ligaments couple to the mask and the exterior surface of the body at a location adjacent to the opening to support a portion of the mask. A coating can be applied to the object, and the mask removed. The final AM object includes a plurality of ligament elements extending from the exterior surface of the body and through the coating adjacent the opening, each ligament element at least partially surrounded by the coating.