A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure.

The present disclosure relates to composite airfoils bonded to a metallic root. A composite body (510) may be formed with a metallic co-molded detail (520). The co-molded detail (520) may be transient liquid phase (TLP) bonded to an attachment feature (530). The attachment feature (530) may allow the composite body (510) to be attached to a rotor (200). The airfoil (500) may also have a metallic edge (550) which is TLP bonded to the composite body (510) via a co-molded edge (540).

A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.

A method for coating a turbine blade of a gas turbine is disclosed. The method includes applying a lacquer coat to a region of the turbine blade, where the lacquer coat includes chromium particles and/or chromium alloy particles, halides, and a binding agent. The method further includes drying the applied lacquer coat at a temperature between 50 C. and 600 C. with disintegration of the binding agent and subsequent reactive connection at a temperature between 900 C. and 1160 C.

A process for providing cooling fluid holes in an airfoil portion of a turbine engine component comprising: positioning a first core with metering/tripping features that form a row of protrusions, and teardrop features that form a fluid passageways, the teardrop features including a central teardrop feature having a trailing edge, a first teardrop feature located on a first side of and spaced from the central teardrop feature, the first teardrop feature having a longitudinal axis and being non-symmetrical about the longitudinal axis, and a second teardrop feature located on a second side of and spaced from the central teardrop feature, the second teardrop feature having a longitudinal axis and non-symmetrical about the longitudinal axis; joining the core to a ceramic core; forming the turbine engine component; removing the core, forming a cooling microcircuit with fluid outlets; and drilling a central portion of the cooling microcircuit forming a converging/diverging outlet.

A wind turbine blade includes one or more electric powered modules powered by light beams so as to provide a galvanic separation between the electric powered modules and a lightning protection system in a wind turbine blade. The modules have a power supply converting an energy source in the form of light beams to electrical power for the one or more modules. A wind turbine and a method for manufacturing a wind turbine blade are also disclosed.

An environmental severity measurement tool measures acceleration along 3 axes to determine shock and vibration affecting a downhole tool in which the environmental severity measurement tool is disposed. The environmental severity measurement tool includes a replaceable battery and electronics disposed within an external housing. A pin provides a way to ensure the environmental severity measurement tool is oriented in a known orientation. Data sampled by the tool can be downloaded from the tool to an external device through a connector port of the electronics. Software in the tool controls the operation of the tool and can be configured from an external device.

A part to modify the profile of an aerodynamic jet, including: a first face configured to be secured on the aerodynamic jet, and a second face defining a modified aerodynamic jet profile, configured to modify an initial profile of the aerodynamic jet.

A propeller blade comprises a root, a tip distal from the root, a trailing edge extending from the root to the tip, a trailing edge, e.g. foam, insert, a shell forming an outer surface of the propeller blade and a plurality of stitches of yarn extending through two parts of the shell adjacent the trailing edge, wherein the yarns do not extend through the trailing edge insert.

A method of manufacture of a cladding body for an edge of an aerofoil, the method including the step of providing a core member shaped to include an elongate recess portion for mounting on the edge of the aerofoil, the elongate recess portion being shaped across its width to define a smoothly curved concave surface. A support member is provided; the support member has a support portion for complementary engagement with the recess portion. Both the support member and the core member are arranged between a pair of opposing membranes. The core member is bonded to each of the pair of membranes to form an intermediate cladding body, wherein the recess portion of the core member is arranged to engage, at least during the bonding step, the support portion to be supported thereby. At least the membranes are shaped using a hot forming process.