Components having an environmental barrier coating and a sintered layer overlying the environmental barrier coating, the sintered layer defining an outer surface having a lower surface roughness than the environmental barrier coating. The sintered layer is formed from a slurry applied to and then sintered on the environmental barrier coating. The sintered layer comprises a primary material, at least one sintering aid dissolved in the primary material, and optionally a secondary material. The sintering aid contains at least one doping composition. The primary material is a rare earth disilicate or a rare earth monosilicate and is doped with the doping composition so as to be either a doped rare earth disilicate or a doped rare earth monosilicate. The optional secondary material is a reaction product of the primary material and any of the sintering aid not dissolved in the primary material.

Provided is a vacuum pump in which no finish processing has to be carried out after shaping of a cylindrical rotor even in use of a cylindrical rotor obtained by shaping a fiber-reinforced plastic material into a cylindrical shape. The vacuum pump has a turbo-molecular pump section and a thread groove pump section. The upper end section of a cylindrical rotor, which is obtained by shaping a fiber-reinforced plastic material into a cylindrical shape, of the thread groove pump section, is joined to the lower end section of a rotor of the turbo-molecular pump section. A joining portion of the rotor of the turbo-molecular pump section and the cylindrical rotor of the thread groove pump section is disposed upstream of an exhaust passage. As a result, finish processing does not have to be carried out after shaping of the cylindrical rotor. If finish processing is performed after shaping of the cylindrical rotor a resin may be coated onto a rugged portion of the cylindrical rotor, or fibers may be helically wound at a winding angle not greater than 45 degrees.

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 method for producing a rotor disk or a rotor blade for a gas turbine compressor stage or turbine stage of an aeroengine, wherein at least one blade groove of the rotor disk for arrangement of a blade foot of a rotor blade for fastening the rotor blade to the rotor disk, or a blade foot of the rotor blade for arrangement in a blade groove of a rotor disk for fastening the rotor blade to the rotor disk is fabricated using an electrochemical material removal and in the axial direction has a profile which is curved once or more.

A shaft failure protection system includes an engine core comprising a turbine, a compressor, and a shaft connecting the turbine and compressor; a first braking element connected to a rotating part of the turbine; and a second braking element connected to a static part of the turbine. The first and second braking elements are arranged at an axial distance under normal operating conditions and configured to contact each other in case of a failure of the shaft and an associated axial displacement of the rotating part. The first braking element includes a first friction material and the second braking element comprises a second friction material, wherein the first and second friction materials each comprise a carbon-silica composite or a carbon-fibre-reinforced carbon. Upon shaft failure and associated axial displacement of the rotating part, the first and second friction materials contact each other to reduce speed of the rotating part.

A combustion engine component is disclosed. The combustion engine component comprises a body that includes a first surface in operative thermal communication with a hot combustion gas, and a second surface in operative fluid communication with a cooling fluid. Also, as disclosed in greater detail below, the second surface includes a first surface contour feature configured to increase a contact angle of a liquid on the second surface.

An impeller manufacturing method includes: integrally forming an impeller by an additive manufacturing method using a metal powder, the impeller including a disk which has a disk shape about an axis, a plurality of blades which are formed on a surface facing a first side in an axial direction of the disk with gaps therebetween in a circumferential direction about the axis, and a cover which covers the plurality of blades from the first side in the axial direction; processing the integrally formed impeller by a hot isostatic pressing; and causing a polishing fluid containing abrasive grains to flow through a flow path formed between the disk, the cover, and the blades in the impeller after the processing with the hot isostatic pressing and while pressurizing the polishing fluid to perform fluid polishing.

A fan blade and a fabricating method thereof are provided. The fan blade includes a rough coating layer on a surface thereof. The rough coating layer includes a plurality of recessed regions. A maximum depth of recess of the recessed regions is between 50 μm to 130 μm.

Methods and systems for manipulating surface topology of additively manufactured fluid interacting structures, such as additively manufactured heat exchangers or airfoils, and associated additively manufactured articles, are disclosed. In one aspect, an article which interacts with a fluid is imparted with surface topology features which affect performance parameters related to the fluid flow. The topological features may be sequenced, combined, intermixed, and functionally varied in size and form to locally manipulate and co-optimize multiple performance parameters at each or selectable differential lengths along a flow path. The co-optimization method may uniquely prioritize selectable performance parameters at different points along the flow path to improve or enhance overall system performance. Topological features may include design features such as dimples, fins, boundary layer disruptors, and biomimicry surface textures, and manufacturing artefacts such as surface roughness and subsurface porosity distribution and morphology.

Provided is a casing 21 for an exhaust turbocharger turbine 2, configured so as to house a turbine rotor 23 to be driven by exhaust gas and form a spiral scroll 22 serving as a path for supplying the exhaust gas to the turbine rotor 23, wherein the scroll 22 includes a first region 222a extending from a spiral origin position 222s to a predetermined angle θ and a second region 222b extending from the predetermined angle θ to a spiral end position 222e, with the surface area of an interior wall thereof decreasing from the spiral origin position 222s toward the spiral end position 222e, and the interior wall at the first region 222a has a lower surface roughness than that at the second region 222b.