A coated component, along with methods of its formation and use, is provided. The coated component may include a substrate having a surface with a plurality of cavities defined therein, a bond coating (e.g., including a silicon material) on the surface of the substrate within the cavities, and an environmental barrier coating over the surface of the substrate and encasing the bond coating within the cavities such that the bond coating, when melted, is contained within the cavities. Such a coated component may be, in one embodiment, a turbine component, such as a CMC component for use in a hot gas path of a gas turbine engine.

Engineered groove features (EGFs) are formed within thermal barrier coatings (TBCs) of turbine engine components. The EGFs are advantageously aligned with likely stress zones within the TBC or randomly aligned in a convenient two-dimensional or polygonal planform pattern on the TBC surface and into the TBC layer. The EGFs localize thermal stress- or foreign object damage (FOD)-induced crack propagation within the TBC that might otherwise allow excessive TBC spallation and subsequent thermal exposure damage to the turbine component underlying substrate. Propagation of a crack is arrested when it reaches an EGF, so that it does not cross over the groove to otherwise undamaged zones of the TBC layer. In some embodiments, the EGFs are combined with engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC.

Turbine and compressor casing abradable component embodiments for turbine engines vary localized porosity or abradability through use of holes or dimple depressions of desired polygonal profiles that are formed into the surface of otherwise monolithic abradable surfaces or rib structures. Abradable porosity within a rib is varied locally by changing any one or more of hole/depression depth, diameter, array pitch density, and/or volume. In various embodiments, localized porosity increases and corresponding abradability increases axially from the upstream or forward axial end of the abradable surface to the downstream or aft end of the surface. In this way, the forward axial end of the abradable surface has less porosity to counter hot working gas erosion of the surface, while the more aft portions of the abradable surface accommodate blade cutting and incursion with lower likelihood of blade tip wear.

A valve device for a cooling water system of a motor vehicle, with a housing including a first connection and a second connection for a first liquid circuit, and a third connection and a fourth connection for a second liquid circuit, wherein the first connection is permanently fluidically connected to the second connection, and with a valve unit including a movably mounted valve element with which a thermally activatable spring element is associated, and which opens a connection between the third connection and the fourth connection in a first end position and cuts off the connection in a second end position. The thermally activatable spring element is arranged in a chamber located between the first connection and the second connection, which is permanently cut off from the third and the fourth connection and which preloads the valve element in the direction of the second end position.

A method may comprise: laying up a first plurality of plies of material comprising thermoplastic resin and fiber to form an inner skin preform, the inner skin preform being a continuous sheet including alternating peaks and valleys; laying up a second plurality of plies of material comprising thermoplastic resin and fiber to form an outer skin preform; and joining the inner skin preform to the outer skin preform.

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.

An airfoil of a propulsion device having a first riblet laminate with a first adhesive layer on at least a first portion of the airfoil surface and a first riblet array sheet disposed on at least a portion of the first adhesive layer. The first riblet array sheet defines a first plurality of contiguous geometric features having rigid peaks and valleys extending in a first rib direction. The first plurality of contiguous geometric features define a total width to total height ratio W:H of about 1:1 to about 2.5:1 with a maximum total height of about 0.65 mm or less. A second riblet array laminate is also disclosed in an embodiment.

This compressor is provided with: a rotor casing that encircles a rotor, which rotates around a rotational axis; an air bleed chamber casing that is provided to the outer peripheral side of the rotor casing and demarcates an air bleed chamber interconnecting to a primary duct via a slot; and an air bleed tube that is connected to the air bleed chamber casing from the outer peripheral side and is provided with an air bleed pathway. In the slot, at which an opening to the primary duct is formed, a large opening, at which the opening area of the opening is locally larger than that of the other positions in the peripheral direction of the opening, is formed at a position in the peripheral direction corresponding to the position at which the air bleed tube is provided.

A core cowl for a turbofan engine may include a plurality of valleys formed in an outer surface of the core cowl. Each valley may include a convex portion upstream of a concave portion, and may be configured to disrupt a shock cell exiting a fan nozzle of the turbofan engine. Associated methods for reducing turbofan engine noise are also described.

An engine component for a gas turbine engine includes a film-cooled wall having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The wall includes one or more film holes that have an outlet provided on the hot surface and a contoured inlet provided on the cooling surface. A contoured portion in the cooling surface encompasses the inlets for two or more film holes in the wall.