A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

A free-tipped axial fan assembly features a shroud barrel comprising an inlet, the radius of said inlet at its upstream end being greater than the radius of said inlet at its downstream end. An angle, in a plane including the fan axis, between the surface of said inlet and the direction of the fan axis varies non-monotonically with respect to a surface coordinate which increases with distance along the surface of the inlet.

A labyrinth seal includes a step-up structure step portion which is a step portion on a high-pressure side, a step-down structure step portion which is a step portion which is a step portion on a low-pressure side, a fin and an annular groove. The fin is arranged on the low-pressure side relative to the step-down structure step portion. The annular groove is arranged in at least a part of a region on the low-pressure side relative to the step-up structure step portion as well as on the high-pressure side relative to the third fin.

A method for protecting a coating on a surface of a component is provided. The method includes a coating step for coating at least a portion of the component with a ceramic slurry. A projecting step is used for projecting a pattern of light onto the component with a lithographic process to expose and solidify a ceramic layer. A removing step is used for removing unexposed portions of the ceramic slurry from the component. A heating step heats the component to sinter the ceramic layer. The ceramic layer is formed with multiple fracture planes.

Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

A centrifugal fan that is light in weight and has a structure that restrains vibration are provided. The centrifugal fan includes a resin upper casing, a resin lower casing, an impeller, a motor, and a circuit board. The impeller, the motor and the circuit board are housed between the resin upper casing and the resin lower casing. Radial ribs and a concentric ribs for reinforcing are formed at a bottom surface of a concave part of the lower casing. Resin pins are provided in a standing manner at these rib parts, and the circuit board is fixed to the lower casing by the resin pins.

A blade body of a turbine blade, which defines an interior cavity fluidly communicative with coolant, is provided. The blade body includes an interior surface and one or more pins extending from the interior surface. The interior surface and the one or more pins are disposable to thermally interact with the coolant. At least one of the one or more pins includes a first section and a second section interposed between the first section and the interior surface. The first section has a larger cross-sectional area than the second section.

A member may have a first major surface and a second major surface. The first major surface may define a plurality of riblets that may extend in the direction of a primary flow. The member may form an array of conduits that extend from an entrance port at the second major surface to an exit port at the first major surface. Each of the exit ports may intersect two or more riblets. Each of the exit ports may intersect a riblet that intersect another of the exit ports.

A blade tip sealing portion forms the distal end of a rotor blade in a turbine engine to reduce or prevent leakage through the blade tip clearance. A rotor assembly comprises a casing, a rotor, and at least one rotor blade coupled to the rotor. The rotor blade comprises a root portion coupled to the rotor, a main airfoil body extending radially from the root portion, and a blade tip sealing portion. The blade tip sealing portion comprises a blade tip platform and a plurality of sealing members. The sealing members are positioned on the blade tip platform at an angle substantially perpendicular to an air flow across the blade tip platform and are spaced to effect overlap of adjacent sealing members in the direction of the air flow.

Presented herein are articles and methods relating to manufactured superhydrophobic, superoleophobic, and/or supermetallophobic surfaces with macro-scale features (macro features) configured to induce controlled asymmetry in a liquid film produced by impinging phase (e.g., impinging droplet(s)) onto the surface, thereby further reducing the contact time between an impinging liquid and the surface.