A non-mechanical fluid transfer device is disclosed herein. The device can include at least one tubular body configured to deliver a fluid, the tubular body having an interior surface, an exterior surface, a proximal end, and a distal end. Additionally, the device can include a series of ratchets disposed along an interior surface of the tubular body such that the fluid moves from the proximal end of the tubular body to the distal end of the tubular body when the interior surface of the tubular body is heated to a temperature at or above the Leidenfrost point of the fluid. Additional aspects are described herein.

A radiation source comprising a fuel source configured to deliver fuel to a location from which the fuel emits EUV radiation. The radiation source further comprises an immobile fuel debris receiving surface provided with a plurality of grooves. The grooves have orientations which are arranged to direct the flow of liquid fuel under the influence of gravity in one or more desired directions.

A radiation source comprising a fuel source configured to deliver fuel to a location from which the fuel emits EUV radiation. The radiation source further comprises an immobile fuel debris receiving surface provided with a plurality of grooves. The grooves have orientations which are arranged to direct the flow of liquid fuel under the influence of gravity in one or more desired directions.

An arrangement for influencing liquid flow comprises a first section selectively configurable to provide a vortex generator surface to induce vortices in the liquid flow. The arrangement further comprises a second section, wherein the first section and second section are movable relative to one another to provide the vortex generator surface.

The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a means for reducing aircraft, missile's, munition's and automobile's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.

Provided is an apparatus for removing thermal stratification generated by turbulent penetration by using a rotation of a pipe wall. The apparatus removes thermal stratification formed in a branch pipe branching from a main pipe through which a high-temperature fluid flows, the apparatus including: a connection body portion including a hollow first body and a hollow second body, the first body being coupled to one side of the branch pipe, and the second body being spaced apart from the first body and connected to other side of the branch pipe; and a hollow rotating part between the first body and the second body, the rotating part rotating around a center of the branch pipe.

A method of forming a microstructured surface includes the operations of depositing electrodes on a surface of a substrate and securing a mold against the surface of the substrate containing the electrodes with a tight contact with the electrodes, the mold containing a plurality of cavities therein. Pressure is applied between the mold and the substrate to force material from the substrate into the plurality of cavities around the electrodes to form a plurality of microfeatures. The mold is separated from the substrate.