A casing that is for a rotating machine and that is configured such that a plurality of housings are linked together, the casing comprising: a first housing including a first connection part that protrudes outward in a radial direction of the rotating machine and that has a first surface extending along the radial direction; a second housing including a second connection part that protrude outward in the radial direction and that has a second surface extending along the radial direction and being in contact with the first surface; and at least one fastening device that fastens the first connection part and the second connection part in the axial direction of the rotating machine, wherein at least one of the first surface or the second surface includes, at least at a portion thereof, a rough surface region having formed therein a plurality of laser irradiation marks formed by irradiation with laser light.

A surface-processed structure includes a plurality of blocks that are three-dimensional objects arranged on a target surface. The plurality of blocks are spaced apart from each other and are arranged side by side in a second direction. Each of the plurality of blocks includes a top face including a plurality of fine grooves. The plurality of fine grooves are spaced apart from each other, are arranged side by side in the second direction, and extend from upstream to downstream in a first direction. A width of each of the plurality of fine grooves in the second direction is less than a width of a block clearance in the second direction. Both end portions of the top face in the second direction are located above bottoms of the plurality of fine grooves in a cross section of the block extending along a plane perpendicular to the first direction.

A surface-processed structure includes a blocks arranged side by side in a first direction parallel to a target surface. The blocks are three-dimensional objects arranged on the target surface. Each of the blocks includes an inclined surface extending from upstream to downstream in the first direction with a distance from the target surface gradually increasing. The inclined surfaces of the blocks are arranged side by side on one line extending in the first direction. Each of the blocks includes a fine grooves provided on the inclined surface. The fine grooves are spaced apart from each other, are arranged side by side in a second direction orthogonal to the first direction, and extend from upstream to downstream in the first direction. The fine grooves extend at a constant depth from an upstream end portion to a downstream end portion of the inclined surface in the first direction.

Methods and systems for treating components are described. The methods include using a system having a controller, a laser applicator, a coating applicator, and a sensor array. The laser applicator, the coating applicator, and the sensor array are arranged on a treatment arm that is controlled by the controller. The method includes scanning a surface to be treated of the component using the sensor array, cleaning the surface to be treated using the laser applicator, defining surface texture patterns, applying laser texturing, and applying a new coating to the surface to be treated using the coating applicator.

A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

A housing element for a pump or of a pump has a housing inner wall defining a flow channel for a fluid medium extending along a central axis. The cross section of the flow channel is greater in a main flow direction and the housing inner wall has a surface structure configured such that it counteracts a return flow counter to the main flow direction along the housing inner wall of the fluid medium. The housing element can act as a pump housing and be combined with a pump.

A flowpath component for a gas turbine engine includes a first platform including a vascular engineered lattice structure, a body extending from, and supported by the first platform. The body is configured to at least partially span a flowpath in an installed position and the vascular engineered lattice structure including at least one purge air inlet, and at least one spent air outlet.

A ceramic matrix composite (CMC) component, such as a turbine blade for a combustion turbine engine that has a fiber-reinforced, solidified ceramic substrate. The substrate has an inner layer of fibers, for enhancing structural strength of the component. An outer layer of fibers defines voids therein. A thermal barrier coat (TBC) is applied over and coupled to the outer layer fibers, filling the voids. The voids provide increased surface area and mechanically interlock the TBC, improving adhesion between the fiber-reinforced ceramic substrate and the TBC.

Turbine and compressor casing abradable components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an array pattern of non-directional depression dimples, or upwardly projecting dimples, or both, in the abradable surface. The dimpled forward zone A surface features reduce surface solidity in a controlled manner, to help increase abradability during blade tip rubbing incidents, yet they provide sufficient material to resist incoming hot working fluid erosion of the abradable surface. In addition, the dimples provide generic forward section aerodynamic profiling to the abradable surface, compatible with different blade airfoil-camber profiles. The aft zone B surface features comprise an array pattern of ridges and grooves.

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.