A method may include cold spraying a masking material on selected locations of a component to form a masking layer, wherein the masking material comprises a metal or alloy; additively manufacturing an additively manufactured portion of the component at locations at which the masking layer is not present; and removing the masking layer from the component. The masking layer may be configured to protect portions of the component by covering or otherwise providing a physical barrier that reduces or prevents material from adhering to unwanted portions of the component during a subsequent manufacturing and/or repair technique. Additionally, the masking layer may be reflective to infrared radiation and/or intimately contact the component and function as a heat sink or thermally conductive layer to transfer heat from the component.

The invention relates to a method for coating a component, which is provided for the hot gas duct of a turbomachine, wherein the coating material is applied onto the uncoated component surface in the form of particles in mixture with a binding agent, and the component with the particle-treated binding agent thereupon then undergoes thermal treatment in such a way that the binding agent is released and the coating material remains on the component.

Additive manufacturing (AM) methods and devices for high-melting-point materials are disclosed. In an embodiment, an additive manufacturing method includes the following steps. (S1) Slicing a three-dimensional computer-aided design model of a workpiece into multiple layers according to shape, thickness, and size accuracy requirements, and obtaining data of the multiple layers. (S2) Planning a forming path according to the data of the multiple layers and generating computer numerical control (CNC) codes for forming the multiple layers. (S3) Obtaining a formed part by preheating a substrate, performing a layer-by-layer spraying deposition by a cold spraying method, and heating a spray area to a temperature until the spraying deposition of all sliced layers is completed. (S4) Subjecting the formed part to a surface modification treatment by a laser shock peening method.

The present disclosure provides a magnetostrictive guided wave sensor and a method for preparing magnetostrictive coating, relating to the field of magnetic functional materials and preparations thereof. The method includes: pretreating a surface of a test piece; and spraying magnetostrictive alloy powder on the pretreated surface of the test piece to form a magnetostrictive coating attached to the pretreated surface. In the magnetostrictive guided wave sensor and the method for preparing magnetostrictive coating according to the embodiments of the present disclosure, by spraying the magnetostrictive coating on the test piece, no coupling agent is required between the probe of the magnetostrictive coating sensor and the test piece, and the magnetostrictive coating can be formed on test pieces of any shape. In addition, the coating has a high bonding strength with the test piece, and has good tissue characteristics and magnetostrictive performance.

Methods of forming a desired geometry at a location on a superalloy part are disclosed. The method may include directing particles of a powder mixture including a low melt temperature superalloy powder and a high melt temperature superalloy powder to the location on the superalloy part at a velocity sufficient to cause the superalloy powders to deform and to form a mechanical bond but not metallurgical bond to the superalloy part. The directing of particles continues until the desired geometry is formed. Heat is applied to the powder mixture on the repair location. The heat causes the low melt temperature superalloy powder to melt, creating the metallurgical bonding at the location. Another method uses the same directing to form a preform for repairing the location on the part. The low melt temperature superalloy powder melts at <1287° C.), and the high melt temperature superalloy powder melts at >1287° C.

A method of forming a passage in a turbine component includes: using an additive manufacturing process to form a first support structure on a first surface of the turbine component; forming a second support structure on a second surface of the turbine component, the second support structure being spaced apart from the first support structure; and forming a passage in the turbine component between the first and second support structures.

Disclosed is a method for manufacturing free-standing cladding tubes with multi-layer structures. According to the method, a cylindrical mandrel substrate defining a hollow cylindrical inner space is provided. A first cold spray powder metal is selected. The cylindrical mandrel substrate is rotated and the first cold spray powder metal is applied to an outer surface of the cylindrical mandrel substrate to form a first layer. The cylindrical mandrel substrate is removed.

The present invention relates to a method and an apparatus for coating large area solid substrates such as flakes, powder, beads, and fibres with metal-based coatings by heating the substrate with a powder mixture including reducible metal oxides and a reducing agent. The method is particularly suited for production of substrates coated with metals, alloys and compounds based on Ti, Al, Zn, Sn, In, Sb, Ag, Co, V, Ni, Cr, Mn, Fe, Cu, Pt, Pd, Ta, Zr, Nb, Rh, Ru, Mo, Os, Re and W.

A linerless engine block includes a polymer matrix composite having an internal surface that defines a bore. The polymer matrix composite has a first thermal conductivity at the internal surface of at least 5 W/m.Math.° C. The linerless engine block also includes a first bond coating disposed on the internal surface within the bore, and a second wear-resistant coating disposed on the first bond coating within the bore such that the second wear-resistant coating is adhered to the polymer matrix composite by the first bond coating. A method of forming the linerless engine block is also described.

Apparatus and methods for additively manufactured structures with augmented energy absorption properties are presented herein. Three dimensional (3D) additive manufacturing structures may be constructed with spatially dependent features to create crash components. When used in the construction of a transport vehicle, the crash components with spatially dependent additively manufactured features may enhance and augment crash energy absorption. This in turn absorbs and re-distributes more crash energy away from the vehicle's occupant(s), thereby improving the occupants' safety.