A portable system is disclosed for collecting a sample from exhaled breath of a subject. Drug substance in the exhaled breath are detected or determined. The sample is collected for further analysis using mass-spectroscopy. The system comprises a sampling unit and a housing arranged to hold the sampling unit, the sampling unit is adapted to collect non-volatile and volatile compounds of the at least one drug substance from the exhaled breath from the subject. The housing has at least one inlet for the subject to exhale into the housing to the sampling unit and at least one outlet for the exhaled breath to exit through.

The invention relates to an airfoil for a compressor of a turbomachine, which extends starting from a blade root between a leading edge and a trailing edge to a blade tip, wherein the leading edge has a leading-edge thickness and the airfoil has a maximum profile thickness, the ratio of which to each other represents a relative leading-edge thickness, and the airfoil has a leading-edge wedge angle.

An impeller includes: a main plate to be rotated; an annular side plate having a suction port for air; and blades in a circumferential direction. Each of the blades has: an inner peripheral end; an outer peripheral end; a sirocco blade portion that includes the outer peripheral end, and forms a forward-swept blade; and a turbo blade portion that includes the inner peripheral end and forms a swept-back blade. The blade has an end portion facing the suction port and a base portion connected to the main plate, and the end portion has a smaller thickness than that of the base portion in the sirocco blade portion. The end portion of the blade has a blade shape, and in the end portion having the blade shape, a first blade thickness of an inner circumferential side of the impeller is greater than a second blade thickness of the outer circumferential side.

A radial fan comprising: a plurality of blades rotatable about an axis of rotation and extending radially from the axis of rotation; characterised in that each of the blades has a transverse profile that is symmetrical about a radial line of symmetry extending through the blade, at least a portion of the profile of each blade being curved.

A turbomachine rotor blade is formed of plural blade sections stacked along an axis extending from a blade root to a blade tip. Each blade section located at various heights along the blade is designed to have a given ratio between a maximum thickness, which is measured between a suction side and pressure side of the blade, and a chord, which is defined by a line connecting a leading edge and a trailing edge of the blade. Each blade section is further designed to have a ratio of the maximum thickness to the chord at a given height of the blade relative to a ratio of the maximum thickness to the chord of another blade section located at a different height of the blade.

A ceiling fan or similar air-moving device can include a motor for rotating one or more blades to drive a volume of air about a space. The blade can include a body having an outer surface with a flat top surface and a flat bottom surface, and a side edge. A chamfered transition can extend between one of the flat top surface or the flat bottom surface, and the side edge. The chamfered transition can include multiple chamfered edges.

An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.

An impeller includes: a disk-shaped hub centered on an axis; and a plurality of blades arranged in a circumferential direction and protruding from a surface of the hub facing one side in a direction of the axis. In a cross-sectional view including a blade height direction which is a direction away from the hub toward a tip of each blade, the blade has a recessed surface curved convexly toward a rear side in a rotational direction. In the cross-sectional view, when a distance between an imaginary line connecting a tip-side edge and a hub-side edge of the blade and a midspan of the blade along a direction perpendicular to the imaginary line is defined as a recess amount, the blade has a portion where the recess amount increases from a leading edge side to a trailing edge side.

An airfoil member having a root end, a tip end, a leading edge, and a trailing edge, the airfoil member including an upper skin; a lower skin; and a support network having a plurality of interconnected support members in a lattice arrangement and/or a reticulated arrangement, the support network being configured to provide tailored characteristics of the airfoil member. Also provided are methods and systems for repairing an airfoil member.

A rotor blade for a turbomachine is provided. The rotor blade includes a platform, an airfoil extending from the platform, and a cooling circuit extending within the platform and the airfoil. The cooling circuit includes a plurality of cooling passages defined by a plurality of ribs. The plurality of ribs includes an offset rib.