Abstract: On an aircraft engine with a shroudless rotor wheel arranged in a flow duct, the flow duct includes a shroud segment (1) formed by a ceramic rubbing coating (3) which, while having good thermal conductivity, is highly-temperature resistant, attaches firmly to the metallic substrate (2) and is abradable by the tips of the rotor wheel to form a sealing gap as narrow as possible, this rubbing coating, owing to the lack of self-insulation, being coolable from a free side of the metallic substrate and, therefore, permitting for working gas temperatures occurring in high-pressure turbines and coating thicknesses sufficient for abrasion.

Abstract: Tobacco products are manufactured by an automatic machine presenting a number of working parts, certain of which consisting in rollers rotatable about mutually parallel axes and carried by a substantially vertical bulkhead of the machine frame, equipped with a protective casing rendered capable of movement by means of a parallelogram linkage between a raised position, clear of the bulkhead, and a lowered position shielding the bulkhead. A horizontal beam associated permanently with the casing carries an upright member serving to support a camera-and-strobe-light assembly; piloted by a master controller, the upright member is traversed along the beam by one motor, and the camera-and-strobe-light assembly along the upright member by another motor, so that the camera can be positioned at any given point on the bulkhead to examine all the working parts.

Abstract: Method for the production of sealing elements on plastics articles. Said method includes the step of producing a film of silicone rubber on the sealing surface of the article. Advantageously, this film is formed by co-moulding or co-extrusion with the plastics article itself. The thickness of the said film may vary from a few tenths of a millimeter to a few millimeters. In the case of cylindrical elements, such as the pistons of the delivery cocks of ice cream machines, this film preferably covers only the side wall or the sealing part of the side wall of the cylindrical element, while in the case of flat elements, this film covers only the sealing surface of this element.

Abstract: Apparatus for moving tubes (10) which are displaceable upon operation of an actuator (40) inside fixed guides (20) integral with the tower (1a) of submarines (1) and the like, said actuator (40) consisting of at least one pair of linear motors (41).

Abstract: In an electronic control system, three-dimensional data sets (data cubes L11-L14) for different power-limiting engine parameters are stored at different engine ratings for setting a respective maximum engine power in relation to flight altitude (ALT), ambient temperature (DTAMB) and flight Mach number (MN) to separately calculate a maximum power corresponding to each parameter. For power reduction due to air bleed, corresponding separate data cubes (L21-L24) are stored. In a comparator, the respective smallest power reduction value is determined and, subsequently, the fuel supply is set according to that power reduction value. Under conforming boundary conditions, the same data cubes (L24) can be stored for different engine ratings. The system requires low storage capacity and low calculating effort.

Abstract: A wear indicating friction disc assembly includes at least two friction discs and may include a plurality of clamping assemblies positioned around a circumference of the friction discs to clamp at least two of the friction discs together. At least one of the clamping assemblies may include a wear indicating washer with a wear indicating portion extending into a portion of one at least one of the friction discs. A height of the wear indicating portion is set to engage the opposing friction member at a predetermined wear level of the friction disc assembly and to emit a detectable signal upon sliding engagement with the opposing friction member.

Abstract: An air-guiding system between a compressor and a turbine of a gas turbine engine includes an air chamber (5) being delimited by the inner casing of the combustion chamber (4) and first and second seals (7, 8) towards the rotating compressor shaft cone (12). An axial thrust compensation chamber (6) is adjoined to said second seal (8) and respectively loaded with the turbine cooling air (B?, C) branched-off from the compressor air. Due to the higher pressure in said axial thrust compensation chamber with respect to said air chamber, the high axial forces are compensated. The air flowing back into said air chamber through said second seal (8) is guided and separated from components (10) and flowing-off air masses by a flow-guiding means (16) in said air chamber. This results in a high rinsing effect, a reduced vortex formation and finally, a reduced thermal stress.

Abstract: When forming metallic components, in particular three-dimensionally curved blades, which constitute a single piece with the blading of turbomachine rotor wheels, the linear oscillation of the electrode acting as a tool is superimposed by a circular oscillation, enabling the electrode to turn into the workpiece conformally with its shape. Further forming is performed by circular oscillation with circular feed in the one and/or the other direction. An embodiment of the corresponding apparatus comprises an electrode holder (9) with linear feed (Zvor) and linear oscillation (Zosz) and a workpiece holder (5) with circular oscillation (Cosz) and circular feed (Cvor).

Abstract: In a machine for making rigid hinge-lid packets, the lid of each packet is folded by a device (9) equipped with a plurality of pockets (2) occupied by respective single packets (P), each presenting a set of end folds (20) that will be bent inwards to form the lid (15), also, a belt conveyor (3) by which the pockets (2) are directed along a predetermined folding path (3b) between an infeed point (10) and an outfeed point (11), a pulley (4) centred on a vertical axis (X) of rotation, and a folder unit (12) mounted to the rotating pulley (4), interacting with a top part (13) of each pocket (2) in such a manner as to engage and bend the end folds (20) of the packet (P). The folding path (3b) coincides with a branch of the belt conveyor (3) looped around the pulley (4).

Abstract: Repair of compressor blades (6) of aircraft engines is performed by build-up welding against an essentially horizontal backing (8) whose surface shape is the exact negative of the respective bottom side of the blade to be repaired. With low rework effort, the blades of blisks can, in the installed state, be repaired or fully restored at any point with high quality upon removal of the damaged portion.

Abstract: A turbine blade locking device axially retains a turbine blade (1) inserted in an axial, profiled slot (10) of a turbine disk (6). The turbine disk (6) is provided with a locking groove (8) passing through the slot (10) and extending radially in the plane of the turbine disk (6). A locking pin (4) is inserted in the locking groove (8) and the blade root (3) is provided at its bottom side with a notch (9) aligning with the locking groove (8). A portion of an elastic element (5) is arranged radially below the locking pin (4) to pre-load the locking pin (4) in a radially outward direction and into the notch (9).

Abstract: A cigarette packet (4) with a cross section of flattened oval profile is fashioned from a diecut blank (1) of essentially elongated rectangular outline referable to a longitudinal axis (16) and comprising, aligned along the axis (16), a central panel (17), two intermediate panels (18, 19) and two end panels (20, 21), each intermediate panel (18, 19) displaying a flattened oval outline and joined to the two contiguous panels (17, 20; 17, 21) along respective rectilinear borders (22) extending transversely to the longitudinal axis (16) and interconnected in pairs by way of respective arcuate borders (23) with no break in linear continuity. The central panel (17) and end panels (20, 21) each present a flat central longitudinal area (24) and two lateral longitudinal bands (25) rendered pliable and thus adaptable to the curvature described by the arcuate borders (23), which they are designed to meet when the packet (4) is erected.

Abstract: A strip of wrapping material is fed and cut into leaves by a unit comprising first and second contrarotating rollers equipped with respective first and second blades of which the first blades operate as a pair to cut the strip transversely into leaves, and the second blades operate as a pair to impress a transverse line on each leaf, this line combining with a longitudinal line, impressed by a further disc cutter, to create a “pull” portion removable from the leaf by tearing. The timing of the second blades can be controlled, so as to adjust the position of the transverse tear-off line on the leaf, by components interacting with the strip along a predetermined feed path extending between two decoiling rollers and a cutting zone that coincides with the line of substantially tangential proximity between the two cutter rollers.

Abstract: Confectionery products (2) are packaged singly in double twist wraps (1) prepared from a strip (3) coated with first longitudinal bands (4) and second transverse bands (5) of adhesive, the transverse bands spaced apart to create adhesive-free zones (6) offered in direct contact to the products (2), and caused to advance along a set path (P) in a given feed direction (D). The strip is prepared with an easy tear point (A) on each second adhesive band (5), consisting of a first notch (7) extending parallel to the longitudinal axis of the strip (3) and a second notch (8) superimposed on the first notch (7); the strip (3) is then cut transversely along the second bands (5) to generate single leaves (11), each presenting an indentation (12) and a projection (13) generated by the second notch (8). The leaf (11) is folded around the product (2) to produce a hermetically sealed wrap (1) designed to tear open from the notches.

Abstract: A turbomachine blade with a profile skeleton line extending along a meridional flow line, the blade being radially divided into at least three zones (Z0, Z1, Z2) with profile skeleton lines of each zone (Z0, Z1, Z2) provided in each zone from the respective radially inner to the radially outer boundary to satisfy the equations: ? * = ? 1 - ? P ? 1 - ? 2 S * = s P S where P is any point of the profile skeleton line, ?1 is angle of inclination at blade leading edge, ?2 is angle of inclination at blade trailing edge, ?* is dimensionless, specific angle of total curvature, S* is dimensionless; specific extension, ?P is angle of tangent at any point P of profile skeleton line to central meridional flow line, sP is extension of profile skeleton line at any point P, and S is total extension of profile skeleton line.

Abstract: A variable stator of a turbomachine with a profile skeleton line extending along a meridional flow line, with the stator being radially divided into at least three zones (Z0, Z1, Z2) and with the respective radial inner and the radial outer profile skeleton line of each zone (Z0, Z1, Z2) being designed such that it satisfies the following equations: ? * = ? 1 - ? P ? 1 - ? 2 S * = S P S where: P is any point of the profile skeleton line, ?1 is the angle of inclination at the stator leading edge, ?2 is the angle of inclination at the stator trailing edge, ?* is the dimensionless, specific angle of the total curvature, S* is the dimensionless, specific extension, ?P is the angle of the tangent at any point P of the profile skeleton line to the central meridional flow line, sP is the extension of the profile skeleton line at any point P, and S is the total extension of the profile skeleton line.

Abstract: A method for hard-material coating or heat treatment of the blade airfoils of blisks for gas turbines provides for partial heat-insulation and cooling of the other blisk parts during the respective process to prevent their properties from being changed by the high temperatures. The apparatus required for this method comprises two or more cooling plates (5 to 7) which are thermally insulated on their outer surfaces and include supporting flanges (20) which heat-conductively locate the blade platforms (3) of the blisks (1). Radially extending cooling medium channels (16) are provided in the cooling plates connected to a cooling medium source to continually apply cooling medium to the inner surfaces of the supporting flanges and the blade platforms.