A method of repairing an article including cleaning a repair area, wherein the repair area comprises a ceramic matrix composite; and depositing a ceramic material in the cleaned repair area using laser assisted chemical vapor deposition. Also disclosed is a repaired ceramic composite produced by this method.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly includes an abradable coating adjacent the contact area, and the abradable coating includes magnetic particles.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly includes an abradable coating adjacent the contact area, and the abradable coating includes magnetic particles.

The invention relates to a guide vane assembly for a turbomachine, comprising a guide vane, which has a guide vane airfoil; and a guide vane holder. The guide vane is mounted in the guide vane holder such that the guide vane can be moved about an axis of rotation. For this purpose, the guide vane has at least one axle element, which is inserted into the guide vane holder in such a way that an outer lateral surface of the axle element faces an inner lateral surface of the guide vane holder. A protective coating is applied to at least parts of the guide vane airfoil. A protective coating is applied to at least one of the lateral surfaces. The invention also relates to a compressor module, a turbomachine, and a method for producing a guide vane assembly.

Methods for forming protective coatings on aerospace components are provided. In one or more embodiments, the method includes exposing an aerospace component to a first precursor and a first reactant to form a first deposited layer on a surface of the aerospace component by a first deposition process (e.g., CVD or ALD), and exposing the aerospace component to a second precursor and a second reactant to form a second deposited layer on the first deposited layer by a second deposition process. The first deposited layer and the second deposited layer have different compositions from each other. The method also includes repeating the first deposition process and the second deposition process to form a nanolaminate film stack having from 2 pairs to about 1,000 pairs of the first deposited layer and the second deposited layer consecutively deposited on each other.

A machine has: an outer member; an inner member mounted for rotation about an axis relative to the outer member; and a seal system. The seal system has: a seal housing mounted to the outer member; one or more seal rings held by the seal housing and having an inner diameter surface; and a seal runner mounted to the inner member and having a first outer diameter surface portion contacting or facing the inner diameter surface of the one or more seal rings. The seal runner has a circumferential array of mounting features. One or more weights are mounted to one or more of the mounting features.

A piston seal assembly for a gas turbine engine includes a seal composed of a nickel-based superalloy; a component in contact with the seal and defining a seal-counterface; and a coating on the seal at the seal-counterface, wherein the coating is a metal alloy binder phase and a hard particle phase distributed through the binder phase.

Methods for forming protective coatings on aerospace components are provided. In one or more embodiments, the method includes exposing an aerospace component to a first precursor and a first reactant to form a first deposited layer on a surface of the aerospace component by a first deposition process (e.g., CVD or ALD), and exposing the aerospace component to a second precursor and a second reactant to form a second deposited layer on the first deposited layer by a second deposition process. The first deposited layer and the second deposited layer have different compositions from each other. The method also includes repeating the first deposition process and the second deposition process to form a nanolaminate film stack having from 2 pairs to about 1,000 pairs of the first deposited layer and the second deposited layer consecutively deposited on each other.

A blade outer air seal assembly includes a support structure and a blade outer air seal having a plurality of segments extending circumferentially about an axis and mounted to the support structure. At least two segments have a base portion extending from a first circumferential side to a second circumferential side, a first protrusion extending from the first circumferential side and having a first slot, and a second protrusion extending from the second circumferential side and having a second slot. A feather seal is arranged in the first slot and the second slot between the at least two segments such that the feather seal is pivotable between first and second positions in response to relative movement between the first and second protrusions.

This disclosure is directed to composites of MAX-phase materials and gold, and methods for preparing the same.