Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have furcated engineered groove features (EGFs) (403, 404, 418, 509, 511, 512) that cut into the outer surface of the component's thermal barrier coating (TBC). In some embodiments, the EGF planform pattern defines adjoining outer hexagons (560, 640, 670, 690, 710). In some embodiments, the EGF pattern further defines within each outer hexagon (560, 640, 670, 690, 710) a planform pattern of adjoining inner polygons (570, 580, 590, 600, 610, 680, 682, 700, 702, 704, 705, 720). At least three respective groove segments (509, 511, 512) within the EGF pattern (506, 507, 508) converge at each respective outer hexagonal vertex (510, 564) or inner polygonal vertex (574, 564, 604, 614) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (σ.sub.A) is furcated (σ.sub.B, σ.sub.C) at each successive vertex juncture.

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 pump impeller, which can be part of a pump, has an impeller surface and blades being arranged on the impeller surface, wherein at least one of the blades is a blade of the first type which has a blade edge which is inclined toward the front in the rotational direction. The pump impeller can also have blades of a first type and of a second type, the blade geometries thereof differing from one another. 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.

In an embodiment, an article comprises a plurality of structural units, wherein each structural unit comprises a first portion; a second portion; wherein the second portion contacts the first portion; and a third portion; wherein the third portion is in communication with the first portion and the second portion and is more compressible than the first portion and the second portion; wherein the first portion comprises a first shape memory alloy having a first preset state and wherein the second portion comprises a second shape memory alloy that has a second preset state; wherein the second preset state is different from the first preset state.

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.

A component according to an exemplary aspect of the present disclosure includes, among other things, a first wall section, a second wall section spaced from the first wall section, a plurality of branches between the first wall section and the second wall section, and a heat transfer device disposed either between adjacent branches of the plurality of branches or inside at least one branch of the plurality of branches.

The present invention is directed to three dimensional (3D) woven lattices for drag and turbulence reduction. 3D woven lattice material can serve as a surface layer that regularizes the flow around a bluff body with beneficial effects on: 1) drag reduction, 2) decrease in turbulence intensity, 3) attenuation of flow-induced vibrations, and 4) aerodynamic noise cancellation. 3-D woven lattice architectures allows for passive flow control (without the need for external energy supply) around bluff bodies with restricted geometry/shape due to their functional requirements such as wind turbine towers, cargo trucks, train cars, etc. The woven material can be easily shaped to fit on various geometries and incorporated in existing manufacturing processes (from composites to metallic plates). Metallic foam and randomly porous materials have been identified in the literature as a promising solution for passive flow control over bluff bodies.

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.

Structures are formed in a shape protruding from a wing surface, and a plurality of riblets are formed in a shape depressed from the wing surface. A first cross section obtained by cutting the structure by a flat face that is parallel to a flow and perpendicularly intersects with the wing surface has an inclined side that extends from a point on the wing surface to a top that is a point apart from the wing surface. An inter-structure flow channel is formed between two adjacent structures among the plurality of structures. The area of a face in one of the two structures and the area of a face in the other structure with which a fluid flowing in the inter-structure flow channel comes into contact are different from each other. Accordingly, peeling of the flow can be suppressed and the frictional resistance of the flow can be decreased.

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.