mhurhangee/patent-ind-claim-en huggingface dataset:
A door assembly , comprising: a door frame ; a door panel ; one or more strut pivotably connected to the door frame and to the door panel ; and at least one door guide , the door guide comprising: a linear slide rail ; a slide saddle ; and a hinge connecting the slide saddle to a first edge face of the door panel , wherein the door panel is movable between an open position and a closed position, wherein the door panel is pivotably movable at an end of the strut and is slidably movable along the linear slide rail , and wherein, when the door panel is in the open position, the door panel is parallel to the linear slide rail and the at least one strut is enclosed between the door panel and the linear slide rail . a door frame ; a door panel ; one or more strut pivotably connected to the door frame and to the door panel ; and at least one door guide , the door guide comprising: a linear slide rail ; a slide saddle ; and a hinge connecting the slide saddle to a first edge face of the door panel , wherein the door panel is movable between an open position and a closed position, wherein the door panel is pivotably movable at an end of the strut and is slidably movable along the linear slide rail , and wherein, when the door panel is in the open position, the door panel is parallel to the linear slide rail and the at least one strut is enclosed between the door panel and the linear slide rail . a linear slide rail ; a slide saddle ; and a hinge connecting the slide saddle to a first edge face of the door panel , wherein the door panel is movable between an open position and a closed position, wherein the door panel is pivotably movable at an end of the strut and is slidably movable along the linear slide rail , and wherein, when the door panel is in the open position, the door panel is parallel to the linear slide rail and the at least one strut is enclosed between the door panel and the linear slide rail .
An aircraft gas turbine including a compressor , a combustor , and a turbine in a casing having a cylindrical shape, the casing having a main unit casing and an external shroud positioned inside of the main unit casing , the aircraft gas turbine comprising: a rotor blade and a nozzle arranged in a combustion gas passage (A), the nozzle positioned on an upstream side of the rotor blade with respect to the flow direction of combustion gas through the combustion gas passage (A), a thick wall part provided on an outer periphery side of the rotor blade in the casing; a cooling passage (53;61;71) provided in the thick wall part to circulate compressed air compressed by the compressor to cool the thick wall part ; and a discharge passage for discharging compressed air having circulated in the cooling passage (53;61;71) to the combustion gas passage (A), wherein the discharge passage is provided between the main unit casing and the external shroud along a longitudinal direction of the gas turbine, an end of the cooling passage (53;61;71) is open to a rear end of the discharge passage with respect to the longitudinal direction, and the discharge passage is in communication with the combustion gas passage (A) via an opening (S) provided in the external shroud , characterized in that the discharge passage is arranged to discharge compressed air having circulated in the cooling passage (53;61;71) to the opening (S) provided on an upstream side of the nozzle in the combustion gas passage (A). a rotor blade and a nozzle arranged in a combustion gas passage (A), the nozzle positioned on an upstream side of the rotor blade with respect to the flow direction of combustion gas through the combustion gas passage (A), a thick wall part provided on an outer periphery side of the rotor blade in the casing; a cooling passage (53;61;71) provided in the thick wall part to circulate compressed air compressed by the compressor to cool the thick wall part ; and a discharge passage for discharging compressed air having circulated in the cooling passage (53;61;71) to the combustion gas passage (A), wherein the discharge passage is provided between the main unit casing and the external shroud along a longitudinal direction of the gas turbine, an end of the cooling passage (53;61;71) is open to a rear end of the discharge passage with respect to the longitudinal direction, and the discharge passage is in communication with the combustion gas passage (A) via an opening (S) provided in the external shroud , characterized in that the discharge passage is arranged to discharge compressed air having circulated in the cooling passage (53;61;71) to the opening (S) provided on an upstream side of the nozzle in the combustion gas passage (A).
High intensity airfield lighting system comprising - a main body ; - a dome securable to the main body , wherein the dome is designed for light transmission and at least partially transparent; - at least one light unit having at least one lighting element and at least one optical element designed to receive light from the lighting element and to emit the light received; - an electronic circuit for powering and driving the lighting elements of the light unit which is in distant position with respect to the light unit ; and - a common heat sink , wherein the common heat sink comprises a first heat sink section carrying the at least one light unit and a second heat sink section carrying the electronic circuit and wherein the common heat sink is provided for cooling both the least one lighting element and the electronic circuit and/or wherein the electronic circuit and the least one lighting element are mounted to the common heat sink , characterized in that a hollow in the second heat sink section and a drainpipe connected to the hollow are provided for draining off entrapped moisture. - a main body ; - a dome securable to the main body , wherein the dome is designed for light transmission and at least partially transparent; - at least one light unit having at least one lighting element and at least one optical element designed to receive light from the lighting element and to emit the light received; - an electronic circuit for powering and driving the lighting elements of the light unit which is in distant position with respect to the light unit ; and - a common heat sink , wherein the common heat sink comprises a first heat sink section carrying the at least one light unit and a second heat sink section carrying the electronic circuit and wherein the common heat sink is provided for cooling both the least one lighting element and the electronic circuit and/or wherein the electronic circuit and the least one lighting element are mounted to the common heat sink ,
A blade of a turbomachine, having a blade leaf , which comprises a flow leading edge , a flow trailing edge and flow guiding surfaces for a process medium extending between the flow leading edge and the flow trailing edge , having a cooling channel integrated in the blade leaf for a cooling medium, wherein in the region of the blade leaf cooling channel portions each extend substantially in the radial direction, wherein adjacent cooling channel portions (26, 28; 28, 30) merge into one another via a deflection channel portion , having a material web extending between the adjacent cooling channel portions (26, 28; 28, 30), wherein the respective material web ends in the region of the respective deflection channel portion , wherein the respective material web between the respective adjacent cooling channel portions (26, 28; 28, 30) has a defined axial width (x) and wherein the respective material web in the region of the respective deflection channel portion has a material thickening enlarging the axial width by at least 20%, characterised in that seen in the axial section the respective material thickening is formed with a rounded corner which is axially at the front and thus facing the flow leading edge, having a rounded corner axially at the rear and thus facing away from the flow leading edge and an axially middle radially outer or radially inner rounded corner arranged seen in the axial direction between the said rounded corners . having a blade leaf , which comprises a flow leading edge , a flow trailing edge and flow guiding surfaces for a process medium extending between the flow leading edge and the flow trailing edge , having a cooling channel integrated in the blade leaf for a cooling medium, wherein in the region of the blade leaf cooling channel portions each extend substantially in the radial direction, wherein adjacent cooling channel portions (26, 28; 28, 30) merge into one another via a deflection channel portion , having a material web extending between the adjacent cooling channel portions (26, 28; 28, 30), wherein the respective material web ends in the region of the respective deflection channel portion , wherein the respective material web between the respective adjacent cooling channel portions (26, 28; 28, 30) has a defined axial width (x) and wherein the respective material web in the region of the respective deflection channel portion has a material thickening enlarging the axial width by at least 20%, characterised in that seen in the axial section the respective material thickening is formed with a rounded corner which is axially at the front and thus facing the flow leading edge, having a rounded corner axially at the rear and thus facing away from the flow leading edge and an axially middle radially outer or radially inner rounded corner arranged seen in the axial direction between the said rounded corners .
A method for providing a secure Fine Timing Measurement, FTM, exchange between two wireless transceivers , said exchange including a FTM request message and a plurality of FTM messages, said method comprising: transmitting a protected FTM range request message with a Dialog token of a FTM frame; receiving a protected FTM range report message from a station , wherein the protected FTM range report message includes FTM information; and authenticating the station based at least in part on the FTM information included in the protected FTM range report message wherein the protected FTM range request message and the protected FTM range report message include one or more encrypted elements, and said FTM request message and said plurality of FTM messages are public action frames. transmitting a protected FTM range request message with a Dialog token of a FTM frame; receiving a protected FTM range report message from a station , wherein the protected FTM range report message includes FTM information; and authenticating the station based at least in part on the FTM information included in the protected FTM range report message wherein the protected FTM range request message and the protected FTM range report message include one or more encrypted elements, and said FTM request message and said plurality of FTM messages are public action frames.
A method of generating an ultrasound image of velocity, the method comprising: transmitting an ultrasound signal (T) to a predetermined point (P ) included in an object and receiving at least three response signals (R 1 , R 2 , R 3 ) reflected from the predetermined point (P ), each of the at least three response signals (R 1 , R 2 , R 3 ) respectively has a Doppler frequency and a reception angle (θ 1, θ 2 , θ 3 ); extracting at least three response signal pairs (R 12 , R 13 , R 23 ) by combining each of the received at least three response signals (R 1 , R 2 , R 3 ) with each of the other signals (R 1 , R 2 , R 3 ); obtaining at least three pieces of prediction vector information (V 12 , V 13 , V 23 ), each of the at least three pieces of prediction vector information (V 12 , V 13 , V 23 ) indicating a prediction velocity magnitude and a prediction velocity direction of the predetermined point, based on reception angles and Doppler frequencies of the response signals included in the at least three response signal pairs (R 12 , R 13 , R 23 ); and determining two-dimensional vector information (V) indicating a velocity magnitude and a velocity direction of the predetermined point, based on the at least three pieces of prediction vector information (V 12 , V 13 , V 23 ). transmitting an ultrasound signal (T) to a predetermined point (P ) included in an object and receiving at least three response signals (R 1 , R 2 , R 3 ) reflected from the predetermined point (P ), each of the at least three response signals (R 1 , R 2 , R 3 ) respectively has a Doppler frequency and a reception angle (θ 1, θ 2 , θ 3 ); extracting at least three response signal pairs (R 12 , R 13 , R 23 ) by combining each of the received at least three response signals (R 1 , R 2 , R 3 ) with each of the other signals (R 1 , R 2 , R 3 ); obtaining at least three pieces of prediction vector information (V 12 , V 13 , V 23 ), each of the at least three pieces of prediction vector information (V 12 , V 13 , V 23 ) indicating a prediction velocity magnitude and a prediction velocity direction of the predetermined point, based on reception angles and Doppler frequencies of the response signals included in the at least three response signal pairs (R 12 , R 13 , R 23 ); and determining two-dimensional vector information (V) indicating a velocity magnitude and a velocity direction of the predetermined point, based on the at least three pieces of prediction vector information (V 12 , V 13 , V 23 ).
A protective fan guard with mounting struts and a fastening device for fastening the mounting struts of the protective fan guard , wherein the mounting struts have a first leg which extends in a longitudinal direction and a second leg which extends in the longitudinal direction parallel to the first leg , which legs engage over a plurality of guard bars of the protective fan guard , the first and second legs each having a free longitudinal end and the fastening device being arranged in the vicinity of the free longitudinal ends of the legs , wherein the fastening device comprises a first fastening sleeve and at least one second fastening sleeve which interlock and form a clamping region which receives the first and second legs and within which the leg ends of the legs are inserted, and wherein the at least two fastening sleeves can be braced axially both against one another and against the legs in order to secure the fan guard, wherein the fastening device is flush with the free longitudinal end of the legs , wherein a vertical axial web is formed on the second fastening sleeve against which the legs are brought into lateral contact, and wherein the two fastening sleeves each have a collar which engages completely over the legs and borders the clamping region .
A method comprising: receiving or transmitting, in a Digital Subscriber Line (DSL) multicarrier communications environment, a plurality of multicarrier symbols in a first data communication state, wherein the first data communication state is a data transmission state, a Showtime state or steady state transmission; determining a SymbolCount, wherein the SymbolCount is a number that indicates a count of multicarrier symbols received or transmitted over a communication line after entering the first data communication state; one or more of determining, storing, measuring and detecting, prior to exiting the first data communication state, the following diagnostic data: a SymbolCount of a last Discrete Multitone Modulation (DMT) symbol received or transmitted prior to exiting the Showtime state, and a SymbolCount of at least one change of a loss of signal (LOS) defect state, wherein a change of the LOS defect state occurs when an LOS defect detection changes from false to true or vice-versa, exiting the first data communication state and entering a second data communication state; and transmitting a message, wherein the message contains information indicating the diagnostic data. receiving or transmitting, in a Digital Subscriber Line (DSL) multicarrier communications environment, a plurality of multicarrier symbols in a first data communication state, wherein the first data communication state is a data transmission state, a Showtime state or steady state transmission; determining a SymbolCount, wherein the SymbolCount is a number that indicates a count of multicarrier symbols received or transmitted over a communication line after entering the first data communication state; one or more of determining, storing, measuring and detecting, prior to exiting the first data communication state, the following diagnostic data: a SymbolCount of a last Discrete Multitone Modulation (DMT) symbol received or transmitted prior to exiting the Showtime state, and a SymbolCount of at least one change of a loss of signal (LOS) defect state, wherein a change of the LOS defect state occurs when an LOS defect detection changes from false to true or vice-versa, exiting the first data communication state and entering a second data communication state; and a SymbolCount of a last Discrete Multitone Modulation (DMT) symbol received or transmitted prior to exiting the Showtime state, and a SymbolCount of at least one change of a loss of signal (LOS) defect state, wherein a change of the LOS defect state occurs when an LOS defect detection changes from false to true or vice-versa, exiting the first data communication state and entering a second data communication state; and transmitting a message, wherein the message contains information indicating the diagnostic data.
Road restraint system comprising a plurality of posts fixed in the ground joined together by at least one current , and longitudinal connecting elements of the posts , characterized in that said longitudinal connecting elements are arranged at the base of the posts, such that in case of impact of a vehicle against the restraint system, said longitudinal connecting elements allow the transfer of the load to the base of the adjacent posts thus increasing the capacity of the system to effectively discharge the loads to ground.
A method for manufacturing a braking band for a brake disc of a disc brake, comprising the following operating steps: a) providing a braking band provided with a base band having an upper face and a lower face arranged on the opposite side to, i.e. opposed to, the upper face , the lower face and upper face each defining, at least partially one of the two sides of the brake disc , the base band being made of titanium or titanium alloy; b) directly depositing, above at least the upper face and/or the lower face , a material in particle form consisting of ceramic and metallic and/or intermetallic particles so to create an upper and/or lower coating layer suitable for withstanding the braking action of the calipers of a disc brake. a) providing a braking band provided with a base band having an upper face and a lower face arranged on the opposite side to, i.e. opposed to, the upper face , the lower face and upper face each defining, at least partially one of the two sides of the brake disc , the base band being made of titanium or titanium alloy; b) directly depositing, above at least the upper face and/or the lower face , a material in particle form consisting of ceramic and metallic and/or intermetallic particles so to create an upper and/or lower coating layer suitable for withstanding the braking action of the calipers of a disc brake.
A vehicular display device comprising: a light shielding housing that is capable of fixing to a surface of a roof of a vehicle on a cabin side and has a concave portion concave upward; an opening portion that is formed at a position facing a rear of the vehicle in the concave portion ; and a display device that has a display surface disposed in the opening portion with the display surface directed to the rear of the vehicle, wherein the concave portion has a first wall surface and a second wall surface positioned closer to the rear of the vehicle than the display surface and facing each other in a vehicle width direction, and a gap (Wd1) between the first wall surface and the second wall surface in the vehicle width direction (W) is larger than a width (Wd2) of the display surface , characterized in that the concave portion further has a third wall surface as a wall surface extending from an upper end of the opening portion toward the rear of the vehicle and facing downward, the third wall surface is an inclined surface directed downward toward the rear of the vehicle, and the opening portion is surrounded from three sides by the first wall surface , the second wall surface , and the third wall surface . a light shielding housing that is capable of fixing to a surface of a roof of a vehicle on a cabin side and has a concave portion concave upward; an opening portion that is formed at a position facing a rear of the vehicle in the concave portion ; and a display device that has a display surface disposed in the opening portion with the display surface directed to the rear of the vehicle, wherein the concave portion has a first wall surface and a second wall surface positioned closer to the rear of the vehicle than the display surface and facing each other in a vehicle width direction, and a gap (Wd1) between the first wall surface and the second wall surface in the vehicle width direction (W) is larger than a width (Wd2) of the display surface , characterized in that the concave portion further has a third wall surface as a wall surface extending from an upper end of the opening portion toward the rear of the vehicle and facing downward, the third wall surface is an inclined surface directed downward toward the rear of the vehicle, and the opening portion is surrounded from three sides by the first wall surface , the second wall surface , and the third wall surface .
Lighting module for a motor vehicle, designed to perform a first non-dazzling lighting function by projecting a beam with a cutoff, and a second long-range lighting function by projecting a second beam without a cutoff, the lighting module comprising at least two light sources , optical deflection devices for optically deflecting the light rays emitted by the light sources , a shaping optic for shaping the deflected rays, and a shield arranged between the optical deflection devices and the shaping optic and able to adopt at least two separate positions, the shield being in a first position of partially blocking the rays so as to achieve the first non-dazzling lighting function and in a free second position so as to achieve the second long-range lighting function, characterized in that each of the light sources is driven so as to modify the luminous intensity emitted by this source on the basis of the position of the shield, in a direction of reducing the intensity or in a direction of increasing the intensity when the shield changes from one given position to the other, two light sources being driven in opposing directions when the shield changes from one given position to another.