mhurhangee/ep-ind-claims huggingface dataset:
A hydraulic machine (7, 8), comprising: a rotation shaft; a cam configured to rotate with the rotation shaft; a plurality of cylinders disposed around the cam each of which includes a distal end portion disposed on an outer side in a radial direction of the rotation shaft, a part of the distal end portion being formed by a first curved surface; a plurality of pistons disposed around the cam so that end portions of the pistons at an inner side in the radial direction contact a cam surface of the cam, the plurality of pistons each being configured to reciprocate in corresponding one of the plurality of cylinders along a direction of a center axis of the cylinder in accordance with rotation of the cam; a stationary member disposed on an outer side of the plurality of cylinders in the radial direction, the stationary member including sockets having second curved surfaces which are engageable with the first curved surfaces of the distal end portions of the cylinders; and a plurality of elastic members for biasing the plurality of cylinders outward in the radial direction so as to force the first curved surfaces of the cylinders against the second curved surfaces of the sockets, wherein the first curved surfaces of the respective cylinders engage with the second curved surfaces of the sockets so that rocking of each of the cylinders is permitted at least in a plane perpendicular to a rotational axis of the rotation shaft, wherein each of the plurality of elastic members is provided for a corresponding one of the plurality of cylinders. a rotation shaft; a cam configured to rotate with the rotation shaft; a plurality of cylinders disposed around the cam each of which includes a distal end portion disposed on an outer side in a radial direction of the rotation shaft, a part of the distal end portion being formed by a first curved surface; a plurality of pistons disposed around the cam so that end portions of the pistons at an inner side in the radial direction contact a cam surface of the cam, the plurality of pistons each being configured to reciprocate in corresponding one of the plurality of cylinders along a direction of a center axis of the cylinder in accordance with rotation of the cam; a stationary member disposed on an outer side of the plurality of cylinders in the radial direction, the stationary member including sockets having second curved surfaces which are engageable with the first curved surfaces of the distal end portions of the cylinders; and a plurality of elastic members for biasing the plurality of cylinders outward in the radial direction so as to force the first curved surfaces of the cylinders against the second curved surfaces of the sockets, wherein the first curved surfaces of the respective cylinders engage with the second curved surfaces of the sockets so that rocking of each of the cylinders is permitted at least in a plane perpendicular to a rotational axis of the rotation shaft, wherein each of the plurality of elastic members is provided for a corresponding one of the plurality of cylinders.
A button lighting structure comprising: a plurality of button members arranged in a matrix with intervals; a light-emitting element disposed in the interval of the plurality of button members; and a button cover member that includes a plate-like portion which has a plurality of openings into which the plurality of button members is inserted, and a guide that guides movement of the button members pushed into the openings, characterized in that: the button cover member includes the guide, which is translucent, and a peripheral wall portion formed along the outer periphery of the plate-like portion, and is configured to irregularly reflect, by the plate-like portion and the peripheral wall portion, light from the light-emitting element disposed to face the plate-like portion, and the button member includes a translucent sidewall portion into which the light, that is emitted from the light-emitting element and that has passed through the guide, enters. a plurality of button members arranged in a matrix with intervals; a light-emitting element disposed in the interval of the plurality of button members; and a button cover member that includes a plate-like portion which has a plurality of openings into which the plurality of button members is inserted, and a guide that guides movement of the button members pushed into the openings, the button cover member includes the guide, which is translucent, and a peripheral wall portion formed along the outer periphery of the plate-like portion, and is configured to irregularly reflect, by the plate-like portion and the peripheral wall portion, light from the light-emitting element disposed to face the plate-like portion, and the button member includes a translucent sidewall portion into which the light, that is emitted from the light-emitting element and that has passed through the guide, enters.
Brazing strip or sheet comprising, preferably consisting of: - a core layer made of aluminum alloy, preferably 3xxx type; - a brazing layer made of aluminum alloy, preferably 4xxx type, cladded on at least one face of the core layer; - optionally an intermediate layer made of aluminum alloy, preferably 3xxx type, cladded on at least one face between the core layer and the brazing layer; - optionally a corrosion protective layer on the optional face of the core layer with no brazing layer; characterized in that the brazing layer alloy comprises, in mass percentages: from 7 to 13% Si, at most 0.8% Fe, at most 0.45% Cu, at most 0.20% Mn, at most 0.15% Mg, at most 0.20% Zn, at most 0.20% Ti, at most 0.04% Bi, from 0.01 to 0.10% Y, from 0.01 to 0.10% Sn, remainder aluminum and impurities. - a core layer made of aluminum alloy, preferably 3xxx type; - a brazing layer made of aluminum alloy, preferably 4xxx type, cladded on at least one face of the core layer; - optionally an intermediate layer made of aluminum alloy, preferably 3xxx type, cladded on at least one face between the core layer and the brazing layer; - optionally a corrosion protective layer on the optional face of the core layer with no brazing layer;
Method for the production of a combustible gas from a fuel, comprising: - the conversion of the fuel, at a temperature that is between 600 and 1000°C and at a pressure that is lower than 10 bar, into at least a combustible gas that comprises CH 4, CO, H 2, CO 2, H 2 O and higher hydrocarbons, - the catalytic conversion of at least part of the higher hydrocarbons present in the combustible gas, at a pressure that is lower than 10 bar, into at least CH 4, CO, H 2, CO 2 and H 2 O, - after the catalytic conversion, the removal of an amount of H 2 O and an amount of CO 2 from the combustible gas at a pressure that is lower than 10 bar, and - after the removal of H 2 O and CO 2, the raising of the pressure of the combustible gas with the aid of a compressor to at least 20 bar, wherein the combustible gas is methanized after the pressure of the combustible gas has been increased by the compressor. - the conversion of the fuel, at a temperature that is between 600 and 1000°C and at a pressure that is lower than 10 bar, into at least a combustible gas that comprises CH 4, CO, H 2, CO 2, H 2 O and higher hydrocarbons, - the catalytic conversion of at least part of the higher hydrocarbons present in the combustible gas, at a pressure that is lower than 10 bar, into at least CH 4, CO, H 2, CO 2 and H 2 O, - after the catalytic conversion, the removal of an amount of H 2 O and an amount of CO 2 from the combustible gas at a pressure that is lower than 10 bar, and - after the removal of H 2 O and CO 2, the raising of the pressure of the combustible gas with the aid of a compressor to at least 20 bar, wherein the combustible gas is methanized after the pressure of the combustible gas has been increased by the compressor.
A cover (12, 112, 212, 312, 412, 530) for magnetizing a tissue-penetrating medical device (10, 30, 50, 130, 230) comprising: a sleeve member (14, 114, 214) having a hollow body 20 with an exterior surface 261, an interior surface, a proximal end (22, 122, 222) and a distal end (21, 221) to form a protective closure over a shaft (34, 134, 234) of a tissue-penetrating medical device (10, 30, 50, 130, 230) having a longitudinal axis, the proximal end (22, 122, 222) of the hollow body 20 providing a receiving space (40, 340) for receiving at least a shaft (34, 134, 234); of the tissue-penetrating medical device (10, 30, 50, 130, 230); one or more magnets (50,150,350) disposed along the sleeve member (14, 114, 214) effective to magnetize the shaft (34, 134, 234); and a magnetic shield (60, 160, 265, 365, 465, 565); characterized in that the magnetic shield (60, 160, 265, 365, 465, 565) is composed of one or more shielding materials spray-coated onto the interior surface of the sleeve member (14, 114, 214), a first face of the one or more magnets (50, 150, 350) being exposed to the receiving space (40, 340) and an opposite face of the one of one or more magnets being exposed to the interior surface of the sleeve with the spray-coated magnetic shield. a sleeve member (14, 114, 214) having a hollow body 20 with an exterior surface 261, an interior surface, a proximal end (22, 122, 222) and a distal end (21, 221) to form a protective closure over a shaft (34, 134, 234) of a tissue-penetrating medical device (10, 30, 50, 130, 230) having a longitudinal axis, the proximal end (22, 122, 222) of the hollow body 20 providing a receiving space (40, 340) for receiving at least a shaft (34, 134, 234); of the tissue-penetrating medical device (10, 30, 50, 130, 230); one or more magnets (50,150,350) disposed along the sleeve member (14, 114, 214) effective to magnetize the shaft (34, 134, 234); and a magnetic shield (60, 160, 265, 365, 465, 565); characterized in that the magnetic shield (60, 160, 265, 365, 465, 565) is composed of one or more shielding materials spray-coated onto the interior surface of the sleeve member (14, 114, 214), a first face of the one or more magnets (50, 150, 350) being exposed to the receiving space (40, 340) and an opposite face of the one of one or more magnets being exposed to the interior surface of the sleeve with the spray-coated magnetic shield.
A rotor blade for a turbomachine, said blade having at its distal end a heel including: - a platform having a first edge on the lower side and a second edge on the upper side, - at least one seal lip (3, 4) having a first end portion on the lower side and a second end portion on the upper side, said seal lip (3, 4) having a seal lip top extending radially outward from said platform between said first and second end portions (301, 302), and for at least one seal lip (3, 4) the heel including at one of the edges (201, 202), at least one portion forming a cup extending along the end portion (301, 302) of the seal lip (3, 4) which corresponds to the edge (201, 202), the portion forming a cup being designed to receive a deposit of an anti-wear material, and characterized in that it includes a layer of anti-wear material deposited by loading with a melted alloy into each cup thus formed. - a platform having a first edge on the lower side and a second edge on the upper side, - at least one seal lip (3, 4) having a first end portion on the lower side and a second end portion on the upper side, said seal lip (3, 4) having a seal lip top extending radially outward from said platform between said first and second end portions (301, 302),
An aircraft comprising a head-up display scenery alignment system the head-up display scenery alignment system is mounted in the aircraft and includes an image projector and a combiner, the combiner is optically located between a user and a scenery of interest, optically transmitting a scene image of the scenery of interest to the user, the image projector projecting an image toward the combiner, the combiner reflecting the image toward the user, the aircraft including a heading angle sensor, determining the heading angle (α) of the aircraft, the head-up display scenery alignment system comprising: a moving mechanism coupled with said combiner; and a processor coupled with said heading angle sensor, with said moving mechanism and with said image projector, said processor being operatively configured to receive heading angle information from said heading angle sensor, said processor being operatively configured to determine the deviation of the heading of the aircraft from the longitudinal axis of the aircraft according to said heading angle information, said processor being operatively configured to direct said moving mechanism, according to said deviation, to move said combiner to a position which is located between said scenery of interest and said user and which aligns the reflection of said image toward said user, with said scene image, wherein said moving mechanism moves said combiner in a horizontal tilt with respect to a horizontal plane of said aircraft. a moving mechanism coupled with said combiner; and a processor coupled with said heading angle sensor, with said moving mechanism and with said image projector, said processor being operatively configured to receive heading angle information from said heading angle sensor, said processor being operatively configured to determine the deviation of the heading of the aircraft from the longitudinal axis of the aircraft according to said heading angle information, said processor being operatively configured to direct said moving mechanism, according to said deviation, to move said combiner to a position which is located between said scenery of interest and said user and which aligns the reflection of said image toward said user, with said scene image, wherein said moving mechanism moves said combiner in a horizontal tilt with respect to a horizontal plane of said aircraft.
A device for heating a medium and air, comprising a heating source and a heat exchanger, the heating source being configured to generate thermal energy by the combustion of a fuel-air mixture, the heat exchanger being configured to serve to heat air passed along an exterior side, the heat exchanger having an interior space configured such that flue gas generated during combustion of the fuel-air mixture enters into it, the heat exchanger having a fin structure on the exterior side, characterized in that at least one electric heating element and at least one medium pipe are provided, the heat exchanger is configured to transmit the thermal energy generated by the heating source to the medium pipe, and the electric heating element is configured to generate thermal energy, the heat exchanger having integral structures for at least partially accommodating both the electric heating element and the medium pipe, the medium pipe being guided - preferably concentrically - around the interior space of the heat exchanger, and the electric heating element being guided - preferably concentrically - around the interior space of the heat exchanger. comprising a heating source and a heat exchanger, the heating source being configured to generate thermal energy by the combustion of a fuel-air mixture, the heat exchanger being configured to serve to heat air passed along an exterior side, the heat exchanger having an interior space configured such that flue gas generated during combustion of the fuel-air mixture enters into it, the heat exchanger having a fin structure on the exterior side, characterized in that at least one electric heating element and at least one medium pipe are provided, the heat exchanger is configured to transmit the thermal energy generated by the heating source to the medium pipe, and the electric heating element is configured to generate thermal energy, the heat exchanger having integral structures for at least partially accommodating both the electric heating element and the medium pipe, the medium pipe being guided - preferably concentrically - around the interior space of the heat exchanger, and the electric heating element being guided - preferably concentrically - around the interior space of the heat exchanger.
A refrigerant compressor having a hermetically sealed compressor housing, in whose interior a piston-cylinder unit, which compresses a refrigerant, is arranged, whose cylinder housing is frontally closed by means of a cylinder head, in which a suction opening and a pressure opening are provided, via which refrigerant is suctioned in via a suction valve through the suction opening and compressed via a pressure valve through the pressure opening, the piston-cylinder unit having at least one piston guided in a piston bore of the cylinder housing, a working space for compressing a refrigerant being formed between the cylinder head and a first front side of the piston, a linear drive being provided, comprising at least one oscillating body enclosed by an exciter winding, which is connected to the piston, in order to move it along a piston longitudinal axis in oscillating manner, the piston-cylinder unit being equipped with at least one permanent magnet arrangement, comprising respectively at least one first permanent magnet arranged on the piston or on a component connected to the piston, characterized in that the at least one permanent magnet arrangement comprises at least one second permanent magnet arranged on the cylinder housing or on a component connected to the cylinder housing, the first permanent magnet and the second permanent magnet pointing toward one another with the same magnetic pole direction in each case, to generate a repelling effect between the two permanent magnets (11, 12) to delimit the piston travel in the region of the top dead center and/or in the region of the bottom dead center upon approach of the first permanent magnet to the second permanent magnet, the component connected to the cylinder housing, on or in which the at least one second permanent magnet is arranged, is the cylinder head, a valve plate is arranged in the cylinder head and the at least one second permanent magnet is arranged on the valve plate, preferably at least sectionally countersunk in the valve plate, in order to delimit the piston travel in the region of the top dead center, the permanent magnets (11, 12) are countersunk into the front side (3a, 3b) of the piston and/or the valve plate so that at least one free space is provided between permanent magnet and piston or valve plate, which communicates with the working space, and this free space extends along the entire periphery of the permanent magnets (11, 12).
A method for determining the influence of a laser machining parameter on a laser machining process using a laser beam, characterised by the following steps: (a) carrying out line-shaped laser machining processes (12; 22; 32) at different values (W 1 to W 5) of the laser machining parameter, wherein the feed speed (v) of the laser beam is increased during the laser machining processes (12; 22; 32) at least to the extent that a machining break occurs; and (b) determining the relationship between the machining lengths, the related machining times (t) or the related break speeds (v A) of the laser machining processes (12; 22; 32) and the laser machining parameter based on the measured machining lengths (L 1 to L 5), the related machining times (t 1 to t 5) or the related break speeds (v A,1 to v A,5) of the laser machining processes (12; 22; 32). (a) carrying out line-shaped laser machining processes (12; 22; 32) at different values (W 1 to W 5) of the laser machining parameter, wherein the feed speed (v) of the laser beam is increased during the laser machining processes (12; 22; 32) at least to the extent that a machining break occurs; and (b) determining the relationship between the machining lengths, the related machining times (t) or the related break speeds (v A) of the laser machining processes (12; 22; 32) and the laser machining parameter based on the measured machining lengths (L 1 to L 5), the related machining times (t 1 to t 5) or the related break speeds (v A,1 to v A,5) of the laser machining processes (12; 22; 32).
An aircraft fuselage for ensuring the integrity of a passenger cabin in the event of a crash, the fuselage comprising: an outer skin that is stiffened by way of a backing structure and that delimits at least one passenger cabin and one cargo hold, in a vertical direction of the fuselage, the cargo hold is arranged below the at least one passenger cabin, the backing structure in the at least one cargo hold, above a cargo-hold floor framework, comprises at least two lateral quasi-joints (16, 18), and below the cargo-hold floor framework comprises at least one further quasi-joint (42, 70, 72, 74, 76), wherein the quasi-joints represent so-called trigger regions that are configured such that in the case of overload the structure in these regions fails earlier than adjacent structural components, thereby the quasi-joints form quasi-axes of rotation for the structural components arranged between them in the longitudinal direction of the fuselage, in the cargo hold, in a longitudinal direction of the fuselage, a multitude of energy absorption devices (44, 58, 84, 86, 88), arranged one behind the other and acting in a transverse direction of the fuselage, are arranged for absorbing tensile loads, wherein the energy absorption devices are configured to absorb kinetic energy associated with a positive displacement or elongation of the cargo hold or cargo hold structure in the transverse direction of the fuselage. an outer skin that is stiffened by way of a backing structure and that delimits at least one passenger cabin and one cargo hold, in a vertical direction of the fuselage, the cargo hold is arranged below the at least one passenger cabin, the backing structure in the at least one cargo hold, above a cargo-hold floor framework, comprises at least two lateral quasi-joints (16, 18), and below the cargo-hold floor framework comprises at least one further quasi-joint (42, 70, 72, 74, 76), wherein the quasi-joints represent so-called trigger regions that are configured such that in the case of overload the structure in these regions fails earlier than adjacent structural components, thereby the quasi-joints form quasi-axes of rotation for the structural components arranged between them in the longitudinal direction of the fuselage, wherein the quasi-joints represent so-called trigger regions that are configured such that in the case of overload the structure in these regions fails earlier than adjacent structural components, thereby the quasi-joints form quasi-axes of rotation for the structural components arranged between them in the longitudinal direction of the fuselage, in the cargo hold, in a longitudinal direction of the fuselage, a multitude of energy absorption devices (44, 58, 84, 86, 88), arranged one behind the other and acting in a transverse direction of the fuselage, are arranged for absorbing tensile loads,