Abstract: a blast nozzle is provided that has a conduit through it for accelerating air applied to the blast nozzle at pressure greater than ambient pressure. The air contains abrasive particles for abrading or “blasting” a workpiece. The conduit includes an inlet portion that converges from an inlet opening for receiving the air, to a throat for accelerating the air to a sonic speed. The conduit also includes an outlet portion that extends from the throat to a nozzle outlet for accelerating the air from the throat to a super-sonic speed at the nozzle outlet. A ratio of area of the nozzle outlet to area of the throat is selected for expansion of the air through the conduit so that air is emitted from the nozzle outlet in a jet at an ambient pressure. The jet imparts drag on the abrasive particles between the nozzle outlet and the workpiece which has been found to improve abrading of the workpiece by the abrasive particles.

Abstract: The present invention relates to a chirally-modified dsRNA agent capable of inhibiting the expression of a target gene. The sense and antisense strands of chirally-modified dsRNA agent independently or in combination comprises one or more site specificsite specific/position specific, chirally-modified internucleotide linkages.

Abstract: The present invention relates to a chirally-modified dsRNA agent capable of inhibiting the expression of a target gene. The sense and antisense strands of chirally-modified dsRNA agent independently or in combination comprises one or more site specific-site specific/position specific, chirally-modified internucleotide linkages.

Abstract: The present invention relates to a chirally-modified dsRNA agent capable of inhibiting the expression of a target gene. The sense and antisense strands of chirally-modified dsRNA agent independently or in combination comprises one or more site specific-site specific/position specific, chirally-modified internucleotide linkages.

Abstract: A gas turbine with a compressor includes at least one row of blades, with the blades having a free end each, with a self-healing abradable coating being provided adjacent to the free end of the blades on an annular casing area and/or an annular drum area.

Abstract: An axial-flow compressor has at least one stator vane row. At least one blade of the stator vane row is provided as a rotating unit (6), with the rotating unit being completely rotatable about a drive axis to act as a rotary compressor and with the drive axis being essentially vertical to a rotary axis of the axial-flow compressor.

Abstract: An axial-flow compressor has at least one stator vane row. At least one blade (8) of the stator vane row (18) is provided as a rotating unit (6), with the rotating unit (6) being completely rotatable about a drive axis (26) and with the drive axis (26) being essentially vertical to a rotary axis (27) of the axial-flow compressor.

Abstract: A thermoelectric generator (1) includes a first electrode (5) in a first chamber (11), a second electrode (6) in a second chamber (14), a heating device (19) and an electrolyte cycle, which connects the first chamber (11) to the second chamber (14). The electrolyte cycle, the first chamber (11) and the second chamber (14) receive an electrolytic solution (16) and the heating device (19) heats the electrolytic solution (16) of the first chamber (11).

Abstract: A gas turbine with a compressor includes at least one row of blades, with the blades having a free end each, with a self-healing abradable coating being provided adjacent to the free end of the blades on an annular casing area and/or an annular drum area.

Abstract: An inner shroud (6) for the stator blades (3) of the compressor of a gas turbine is a plastic component and includes certain additives, which may be concentrated in partial areas for specific functionality, and/or pre-manufactured inserts for sealing, ensuring sliding properties, wear protection and/or setting heat expansion. Such an inner shroud made of plastic material fulfills all requirements usually imposed on inner shrouds made of metal, while being simply producible and having low weight.

Abstract: A screw-type gap control arrangement for a gas turbine with at least one row of variable vanes 2 and with a gas-wetted surface 4 adjacent to a blade row, wherein the surface 4 has essentially the form of a spherical surface ring and, at the same time, a contraction of a gas path with an aerodynamically favorable form of an annulus is obtained.

Abstract: For precision balancing of the rotor (3) that, in fully assembled condition of a gas turbine engine, is encompassed by an inner and an outer case, inserts (7) with a through hole (11) and a female threaded section are positioned at an even spacing in at least one circumferential groove (6) of the rotor disks (5) that receives the roots of the rotor blades (4). A temporarily installed guide tube (15) that runs through the openings (13, 14) connects to the through hole that in a certain rotor position is in line with the openings (13, 14) in the inner and outer cases (1, 2) for inserting and screwing in a balancing screw (16).

Abstract: An inner shroud (6) for the stator blades (3) of the compressor of a gas turbine is a plastic component and includes certain additives, which may be concentrated in partial areas for specific functionality, and/or pre-manufactured inserts for sealing, ensuring sliding properties, wear protection and/or setting heat expansion. Such an inner shroud made of plastic material fulfills all requirements usually imposed on inner shrouds made of metal, while being simply producible and having low weight.