A method for detecting at least one roughness in a face of an abradable layer in a fan casing is provided. The method includes a step of depositing on the abradable layer a first coating and a second coating covering the first coating. The first and second coatings have respective thicknesses (N1, N2) and a physical appearance that differ from one another. Local appearance of the first coating is indicative of a need for a localized touch-up, and local disappearance of the first coating and the second coating is indicative of a need for a localized replacement of the abradable layer.

A blade for fluid catalytic cracking (FCC) flue hot gas expander with a layer of hard abrasive material localized on the blade tip that contributes to reducing the accumulation of FCC catalyst residuals in the expander.

A blade comprises an airfoil having a root end and a tip. A metallic substrate is along at least a portion of the airfoil. An abrasive tip coating comprises an abrasive and an aluminum-based matrix. An aluminum-based base layer is between the tip coating and the substrate.

A turbine shroud segment for use in a gas turbine engine includes a ceramic shroud segment formed to define a circumferentially extending channel that opens radially inwardly and a layer of abradable material that extends axially along a radial inner surface of the ceramic shroud segment to provide a flow path surface of the turbine shroud segment.

An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.

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.

An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.

Described is a blade for a high-speed turbine stage of an aircraft gas turbine, in particular of an aircraft engine, the blade including a radially inner blade root, and an airfoil extending radially outwardly from the blade root. It is provided that the blade be shroudless and that the airfoil have a radially outer end portion that is positionable opposite a rub surface when the blade is in an installed state, and that the airfoil have a radially inner chord length that is at least 1.1 times, preferably at least 1.2 times, in particular at least 1.3 times a radially outer chord length, the inner chord length being measured at the airfoil directly above the blade root, and the outer chord length being measured at the airfoil in the region of or below the end portion.

A method for detecting at least one roughness in a face of an abradable layer in a fan casing is provided. The method includes a step of depositing on the abradable layer a first coating and a second coating covering the first coating. The first and second coatings have respective thicknesses (N1, N2) and a physical appearance that differ from one another. Local appearance of the first coating is indicative of a need for a localized touch-up, and local disappearance of the first coating and the second coating is indicative of a need for a localized replacement of the abradable layer.