mhurhangee/ep-ind-claims huggingface dataset:
A combustion engine operable in at least a first gaseous fuel mode and a second gaseous fuel mode, comprising: at least one cylinder; an inlet valve configured to supply the at least one cylinder with intake air: an outlet valve configured to discharge exhaust from the at least one cylinder; and a control device configured to adjust at least an inlet valve closing timing of the inlet valve, wherein the control device is configured to adjust the inlet valve closing timing to a first inlet valve closing timing in the first gaseous fuel mode, and to a second inlet valve closing timing in the second gaseous fuel mode, the second inlet valve closing timing being earlier than the first inlet valve closing timing, wherein the first gaseous fuel mode is a medium load gaseous fuel mode, and the second gaseous fuel mode is a high load gaseous fuel mode, and wherein the control device is configured to switch from the first inlet valve closing timing to the second inlet valve closing timing when an engine load exceeds a predetermined first load threshold of between 50% and 99%, for example, between 70% and 90%, in particular, 80%, of the full engine load. at least one cylinder; an inlet valve configured to supply the at least one cylinder with intake air: an outlet valve configured to discharge exhaust from the at least one cylinder; and a control device configured to adjust at least an inlet valve closing timing of the inlet valve, an outlet valve configured to discharge exhaust from the at least one cylinder; and a control device configured to adjust at least an inlet valve closing timing of the inlet valve, wherein the control device is configured to adjust the inlet valve closing timing to a first inlet valve closing timing in the first gaseous fuel mode, and to a second inlet valve closing timing in the second gaseous fuel mode, the second inlet valve closing timing being earlier than the first inlet valve closing timing, wherein the first gaseous fuel mode is a medium load gaseous fuel mode, and the second gaseous fuel mode is a high load gaseous fuel mode, and wherein the control device is configured to switch from the first inlet valve closing timing to the second inlet valve closing timing when an engine load exceeds a predetermined first load threshold of between 50% and 99%, for example, between 70% and 90%, in particular, 80%, of the full engine load.
Gaseous composition containing a gaseous argon and xenon mixture for use by inhalation to prevent or treat at least one neurological side-effect of septic shock in a patient.
A cockpit display system onboard an aircraft, the cockpit display system comprising: an Instrument Landing System receiver configured to detect Glide Slope (G/S) signals during an ILS approach flown by the aircraft and terminating at a destination runway; a cockpit display device on which a Synthetic Vision Primary Flight Display (SV-PFD) is generated, the SV-PFD including a Synthetic Visions Systems scene presented from an SVS viewpoint; and a controller operably coupled to the cockpit display device and to the ILS receiver; characterized in that the controller is configured to repeatedly: selectively perform a G/S validation algorithm to determine the validity of the G/S signals received during the ILS approach; and if determining that the G/S signals are valid, update a vertical component of the SVS viewpoint during the ILS approach based upon the G/S signals. an Instrument Landing System receiver configured to detect Glide Slope (G/S) signals during an ILS approach flown by the aircraft and terminating at a destination runway; a cockpit display device on which a Synthetic Vision Primary Flight Display (SV-PFD) is generated, the SV-PFD including a Synthetic Visions Systems scene presented from an SVS viewpoint; and a controller operably coupled to the cockpit display device and to the ILS receiver; characterized in that the controller is configured to repeatedly: selectively perform a G/S validation algorithm to determine the validity of the G/S signals received during the ILS approach; and if determining that the G/S signals are valid, update a vertical component of the SVS viewpoint during the ILS approach based upon the G/S signals. selectively perform a G/S validation algorithm to determine the validity of the G/S signals received during the ILS approach; and if determining that the G/S signals are valid, update a vertical component of the SVS viewpoint during the ILS approach based upon the G/S signals.
A compact drum kit comprising: a body having a hollow interior defined by a top comprising a snare drum, a bottom, three or more sides connecting the top and bottom, and a sound hole; a plurality of upward extending component mounting shafts and a plurality of leg shafts; and one or more percussion modules (150, 160, 170) that attach to one or more of the plurality of component mounting shafts, wherein each percussion module (150, 160, 170) is configured to produce a sound in response to being struck or scraped; and a kick pedal including a beater positioned to strike a first side of the three or more sides and produce a sound; characterized in that the leg shafts are mounted in the hollow interior of the body and protrude through a plurality of openings in the body; and the upward extending component mounting shafts are mounted in the hollow interior of the body and protrude through a plurality of elongated openings in the body, wherein each of the plurality of component mounting shafts is straight for a portion of its length and curved for another portion of its length so that the respective component mounting shafts are lockable at various heights from completely recessed within the body to fully extended at the full length of the component shaft. a body having a hollow interior defined by a top comprising a snare drum, a bottom, three or more sides connecting the top and bottom, and a sound hole; a plurality of upward extending component mounting shafts and a plurality of leg shafts; and one or more percussion modules (150, 160, 170) that attach to one or more of the plurality of component mounting shafts, wherein each percussion module (150, 160, 170) is configured to produce a sound in response to being struck or scraped; and a kick pedal including a beater positioned to strike a first side of the three or more sides and produce a sound; characterized in that the leg shafts are mounted in the hollow interior of the body and protrude through a plurality of openings in the body; and the upward extending component mounting shafts are mounted in the hollow interior of the body and protrude through a plurality of elongated openings in the body, wherein each of the plurality of component mounting shafts is straight for a portion of its length and curved for another portion of its length so that the respective component mounting shafts are lockable at various heights from completely recessed within the body to fully extended at the full length of the component shaft.
An assembly consisting of a mounting component for mounting at least one bearing (7, 8) of a turbomachine shaft, said turbomachine comprising an external structure enveloping its moving parts and a casing carrying said bearing, these two elements being intended to be connected to one another by said mounting component, and of a support component (11, 21) configured to be fixed to the external structure of the turbomachine and to form an abutment for said mounting component, said mounting component comprising at least one passage through which the gases from the engine pass and connecting components (3, 4) which are configured to attach said passage firstly to the external structure of the engine and secondly to said casing, at least one of the connecting components being flexible so as to allow a radial movement of said passage, the amplitude of said radial movement being limited by at least one of the elements (2, 3, 4) of the mounting component coming into abutment with an abutment carried by said support component, characterized in that said support component comprises a rear extension extending longitudinally downstream beyond the longitudinal extension of said passage, with reference to the direction of the axis of rotation of the turbomachine, so as to generate an annulus that can act as a turbine shroud for a turbine wheel of the turbomachine.
A method for producing a hollow component made of a composite material, comprising the steps of: - producing or providing a winding mandrel (12, 13, 14, 23) having at least one water-soluble portion (13, 23); - winding filaments or fibers of the composite material around the winding mandrel (12, 13, 14, 23) to form an assembly comprising the winding mandrel (12, 13, 14, 23) and the hollow component wound around the winding mandrel (12, 13, 14, 23); - subjecting the assembly consisting of the winding mandrel (12, 13, 14, 23) and the hollow component to a heat treatment to consolidate the shape of the hollow component; - dissolving the at least one water-soluble portion (13, 23) of the winding mandrel (12, 13, 14, 23), by immersing the assembly consisting of the winding mandrel (12, 13, 14, 23) and the hollow component in water or in an aqueous solution; characterized in that said at least one water-soluble portion (13, 23) has a body made as a mesh or a three-dimensional grid in which a fluid can flow. - producing or providing a winding mandrel (12, 13, 14, 23) having at least one water-soluble portion (13, 23); - winding filaments or fibers of the composite material around the winding mandrel (12, 13, 14, 23) to form an assembly comprising the winding mandrel (12, 13, 14, 23) and the hollow component wound around the winding mandrel (12, 13, 14, 23); - subjecting the assembly consisting of the winding mandrel (12, 13, 14, 23) and the hollow component to a heat treatment to consolidate the shape of the hollow component; - dissolving the at least one water-soluble portion (13, 23) of the winding mandrel (12, 13, 14, 23), by immersing the assembly consisting of the winding mandrel (12, 13, 14, 23) and the hollow component in water or in an aqueous solution;
An aircraft airframe comprising: a frame; a beam mounted generally transverse to said frame at a predetermined rotational failure location about which the beam is capable of hinging relative to the frame; characterized in that it comprises a collapsible member configured to provide structural support for an upper deck as a portion of the airframe during normal operational conditions, said collapsible member is mounted adjacent said beam capable of collapsing in a controlled manner in response to a high sink rate impact event above a predetermined threshold load value such that upon such impact event said beam is articulated about said predetermined rotational failure location in response to the impact event. a frame; a beam mounted generally transverse to said frame at a predetermined rotational failure location about which the beam is capable of hinging relative to the frame; characterized in that it comprises a collapsible member configured to provide structural support for an upper deck as a portion of the airframe during normal operational conditions, said collapsible member is mounted adjacent said beam capable of collapsing in a controlled manner in response to a high sink rate impact event above a predetermined threshold load value such that upon such impact event said beam is articulated about said predetermined rotational failure location in response to the impact event.
A rotor blade comprising: a blade platform having a blade root extending from the blade platform for receiving in a blade slot of a rotor disk; and a blade land segment (56, 116) extending from the blade root, wherein the blade land segment (56, 116) defines a seal land for contacting a brush seal (46, 106) extending from a stationary turbine engine component, wherein the blade land segment (56, 116) includes two first interlocking features each for interfitting with respective second interlocking features of a respective disk land segment (54; 114) of the rotor disk, wherein at least a portion of each first interlocking feature overlaps with at least a portion of the respective second interlocking feature, and characterized in that the blade land segment is non-symmetrical relative to a radial axis extending substantially along the span of the rotor blade. a blade platform having a blade root extending from the blade platform for receiving in a blade slot of a rotor disk; and a blade land segment (56, 116) extending from the blade root, wherein the blade land segment (56, 116) defines a seal land for contacting a brush seal (46, 106) extending from a stationary turbine engine component, wherein the blade land segment (56, 116) includes two first interlocking features each for interfitting with respective second interlocking features of a respective disk land segment (54; 114) of the rotor disk, wherein at least a portion of each first interlocking feature overlaps with at least a portion of the respective second interlocking feature, and characterized in that the blade land segment is non-symmetrical relative to a radial axis extending substantially along the span of the rotor blade.
A device for dispensing active ingredient-containing or active ingredient-carrying strips, having a housing, in which housing there is arranged a spool chamber for accommodating an active ingredient-containing or active ingredient-carrying band, in which housing there is mounted a wheel transmission with an output roller for conveying the band, and in which housing there is arranged a severing device for severing the strips from the band, wherein - an indexing coupling mechanism is positioned upstream of the wheel transmission, - the indexing coupling mechanism has a manually actuatable triggering element, and - the output roller is driveable in incremental steps by means of the indexing coupling mechanism, and - the triggering element is configured such that a manual actuation of the triggering element triggers an indexing of the indexing coupling mechanism and thus an incremental movement of the output roller, characterized in that a severing device for severing the strips from the band is arranged in the housing. - an indexing coupling mechanism is positioned upstream of the wheel transmission, - the indexing coupling mechanism has a manually actuatable triggering element, and - the output roller is driveable in incremental steps by means of the indexing coupling mechanism, and - the triggering element is configured such that a manual actuation of the triggering element triggers an indexing of the indexing coupling mechanism and thus an incremental movement of the output roller,
A gas shield arrangement (121, 122) for a gas turbine engine, the gas shield arrangement comprising: a first gas shield arranged to cover an inlet of a gas flow path of the gas turbine engine; a second gas shield arranged to cover a first outlet of the gas flow path of the gas turbine engine; the first gas shield comprising a first valve for controlling a flow of fluid through the first gas shield; the second gas shield comprising a second valve for controlling a flow of fluid through the second gas shield; a reservoir including one or more containers comprising one or more fluids for enabling one or more actions to be performed within the gas flow path; and a pump for pumping fluid from the reservoir to one of: the first valve and the second valve, to provide a controlled atmosphere within the gas flow path, at least some of the fluid returning to the reservoir from the other of: the first valve and the second valve. a first gas shield arranged to cover an inlet of a gas flow path of the gas turbine engine; a second gas shield arranged to cover a first outlet of the gas flow path of the gas turbine engine; the first gas shield comprising a first valve for controlling a flow of fluid through the first gas shield; the second gas shield comprising a second valve for controlling a flow of fluid through the second gas shield; a reservoir including one or more containers comprising one or more fluids for enabling one or more actions to be performed within the gas flow path; and a pump for pumping fluid from the reservoir to one of: the first valve and the second valve, to provide a controlled atmosphere within the gas flow path, at least some of the fluid returning to the reservoir from the other of: the first valve and the second valve.
A method for the direct detection of the presence of a cavity in a drill-hole intended for the reception of a reinforcement member (7, 40), which method comprises: - the injection of hardening grout into the drill-hole, - the introduction of a reinforcement member (7, 40) into the drill-hole, - the introduction of a pressurised medium into the drill-hole, and - the measurement of a change in pressure in the medium or the detection of a flow of medium, whereby a fall in pressure or the presence of a flow of medium indicates the presence of a cavity. - the injection of hardening grout into the drill-hole, - the introduction of a reinforcement member (7, 40) into the drill-hole, - the introduction of a pressurised medium into the drill-hole, and - the measurement of a change in pressure in the medium or the detection of a flow of medium, whereby a fall in pressure or the presence of a flow of medium indicates the presence of a cavity.
Disc brake comprising a brake calliper, wherein two brake linings are arranged which are suitable for being pressed, in operation, against a brake disc, whereof one lining, on the operating side, can be operated via at least one adjusting spindle by means of a brake application device, and wherein said adjusting spindle is passed through an opening of a closing cover, that is limited by an angled collar, with said closing cover closing an accommodating space of said brake calliper, and wherein, for sealing of said accommodating space, a bellows bears against said adjusting spindle, on the one hand, and, on the other side, by an edge region against said collar, where a secondary seal is moreover held, which is concentrically arranged relative to said bellows and bears against said adjusting spindle, characterised in that said pot-shaped secondary seal is applied by injection as plastic part to said collar of said metal closing cover.
Method for verifying an element of an industrial plant by means of a mobile operating device, wherein an element-specific identification is defined on the element, comprising the method steps: - Non-contact reading of the identification of the element by the operating device; - Identification of the element by comparing the identification read in with the defined identification of the element; - Transfer of at least one item of element-specific information for the identified element to the operating device, wherein the element-specific information is an actual state variable of the element during the operation of the industrial plant, especially at certain points during operation; and - Output of the transferred element-specific information at the operating device. - Non-contact reading of the identification of the element by the operating device; - Identification of the element by comparing the identification read in with the defined identification of the element; - Transfer of at least one item of element-specific information for the identified element to the operating device, wherein the element-specific information is an actual state variable of the element during the operation of the industrial plant, especially at certain points during operation; and - Output of the transferred element-specific information at the operating device.
Arrangement of at least two motor-adjacent waste gas system components for a combustion engine of a motor vehicle, which components are arranged one behind the other downstream of the combustion engine of the motor vehicle and are connected to one another by means of a first connecting body so that a waste gas of the combustion engine can be guided through the at least two waste gas system components one behind the other in the direction of an exhaust outlet system, wherein the two waste gas system components are arranged downstream of a manifold device of the combustion engine by means of a second connecting body, and a length from an outlet of the manifold device to an inlet of the waste gas system component arranged at the most upstream position is at most 0.07 m, wherein the first waste gas system component is a three-way catalytic converter and the second waste gas system component is a particulate filter, wherein the three-way catalytic converter is arranged at the most upstream position in the waste gas flow direction and the particulate filter is arranged via the first connecting body downstream of the three-way catalytic converter, characterized in that the three-way catalytic converter is longer than it is wide and the particulate filter is wider than it is long, the dimensions of the three-way catalytic converter are as follows: width: 0.110 to 0.125 m and length: 0.144 to 0.157 m, and the dimensions of the particulate filter are as follows: width: 0.124 to 0.137 m and length: 0.121 to 0.132 m. wherein the first waste gas system component is a three-way catalytic converter and the second waste gas system component is a particulate filter, wherein the three-way catalytic converter is arranged at the most upstream position in the waste gas flow direction and the particulate filter is arranged via the first connecting body downstream of the three-way catalytic converter, characterized in that the three-way catalytic converter is longer than it is wide and the particulate filter is wider than it is long, the dimensions of the three-way catalytic converter are as follows: width: 0.110 to 0.125 m and length: 0.144 to 0.157 m, and the dimensions of the particulate filter are as follows: width: 0.124 to 0.137 m and length: 0.121 to 0.132 m.