Abstract: To improve precision in decision in a technique for deciding an activity area of a target user, based on information of another person, the present invention provides a processing apparatus 10 including: a determination unit 11 that determines one or a plurality of reference users having a predetermined relationship with a target user whose activity area in a target period is to be estimated, based on post information posted on social media by each user within a search period being set based on the target period; an estimation unit 12 that estimates an activity area of the reference user in the target period; and a decision unit 13 that decides an activity area of the target user in the target period, based on an activity area of the reference user in the target period.

Abstract: An information processing apparatus (2) includes: an obtaining unit (211) that obtains an infection information relating to an infected person that catches an infection disease; and an identifying unit (213) that identifies, as a contact person that possibly contacts the infected person, at least one target person staying in a stay area in which the infected person stays in at least a part of a time period during which the infected person stays in the stay area from a plurality of target persons based on the infection information and a history information (221) that is generated based on a plurality of target person images (IMG) that indicate the plurality of target persons, respectively.

Abstract: An information processing system (SYS) includes: a plurality of gate apparatuses (1) that are respectively placed at a plurality of lanes (L) through each of which a target person (P) can pass; a thermal camera (3) that is configured to generate a body temperature information (IMG_T) indicating a body temperature of the target person by capturing an image of the target person included in an imaging range (TRG) thereof, the imaging range including at least a part of each of the plurality of lanes; and an information processing apparatus (4) that obtains the body temperature information from the thermal camera.

Abstract: A sealing apparatus includes a sealing portion configured to be positioned between a platform of a turbine blade and an inner shroud of a turbine vane of a turbine, and an acoustic damper having a closed space portion which is configured to communicate, via an opening, with a disc cavity configured to be positioned between the turbine blade and the turbine vane.

Abstract: An injection device, a combustor, and a rocket engine include a device main body partitioned into a fuel manifold and an oxidant manifold, and a plurality of injectors arranged at predetermined intervals in the device main body to inject fuel and oxidant into a combustion chamber, each of the injectors includes a LOx channel including a proximal end portion communicating with the oxidant manifold and a distal end portion communicating with the combustion chamber, a restrictor provided on the proximal end portion of the LOx channel and a GH2 channel including a proximal end portion communicating with the fuel manifold and a distal end portion communicating with the combustion chamber, and the restrictors have different shapes.

Abstract: An injection device, a combustor, and a rocket engine include a device main body partitioned into a fuel manifold and an oxidant manifold, and a plurality of injectors arranged at predetermined intervals in the device main body to inject fuel and oxidant into a combustion chamber, each of the injectors includes a LOx channel including a proximal end portion communicating with the oxidant manifold and a distal end portion communicating with the combustion chamber, a restrictor provided on the proximal end portion of the LOx channel and a GH2 channel including a proximal end portion communicating with the fuel manifold and a distal end portion communicating with the combustion chamber, and the restrictors have different shapes.

Abstract: An exhaust flue includes an exhaust chimney body, and an open end multi-hole area. The exhaust chimney body defines a passage for discharging exhaust gas. The open end multi-hole area is an area in which multiple holes are defined around a total circumference of an open end of the exhaust chimney body.

Abstract: In a sealing apparatus for a gas turbine, a gas turbine, and an aircraft engine: a first sealing portion provided between a platform of a turbine blade and an inner shroud of a turbine vane of a turbine, and an acoustic damper having a closed space portion communicating, via an opening, with a disc cavity between the turbine blade and the turbine vane are provided. Accordingly, improvement in gas turbine efficiency is aimed for, by reduction of entrance of combustion gas into a turbine body being enabled with a small amount of purge air.

Abstract: In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

Abstract: In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

Abstract: An exhaust flue (40) includes an exhaust chimney body (43), and an open end multi-hole area (51). The exhaust chimney body (43) is a passage for discharging exhaust gas. The open end multi-hole area (51) is an area in which multiple holes (50) have been opened around the total circumference of an open end (44) of the exhaust chimney body (43). The exhaust flue (40) is capable of minimizing the release of noises with low-frequency components to the outside by means of a simple construction in which holes (50) are opened in the exhaust chimney body (43).

Abstract: In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

Abstract: In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor (3) is provided with a first box body (30), which is installed outside an object body (20) such as a combustor basket (6), a transition piece (7) or a bypass duct (11) so as to form a first internal space (31) having a predetermined capacity; and a first throat (32) having a predetermined length which has one end (32a) open to a side wall (20a) of the object body (20) and has the other end (32b) open to a first internal space (31); wherein, a first resistive element (33) having a multiple number of through-holes is inserted and engaged to one end (32a).

Abstract: In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

Abstract: A gas turbine combustor includes a combustion liner in which a combustion region is formed; and a housing provided for a wall of the combustion liner in a predetermined circumferential region of the combustion liner to form a resonance space between the combustion liner and the housing. The combustion region and the resonance space are connected by a plurality of combustion liner through-holes, and a circumferential length of the housing is longer than a diameter of the combustion liner.

Abstract: In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor (3) is provided with a first box body (30), which is installed outside an object body (20) such as a combustor basket (6), a transition piece (7) or a bypass duct (11) so as to form a first internal space (31) having a predetermined capacity; and a first throat (32) having a predetermined length which has one end (32a) open to a side wall (20a) of the object body (20) and has the other end (32b) open to a first internal space (31); wherein, a first resistive element (33) having a multiple number of through-holes is inserted and engaged to one end (32a).

Abstract: The objective is to provide a gas turbine and the combustor thereof in which super high frequency combustion oscillation and the generation of NOx are reduced. The fluctuation in pressure which induces the fluctuation in heat liberation is suppressed in the gas turbine combustor comprising a plurality of main fuel supply nozzles, each having a premixing nozzle at the top end part thereof, by providing in the space upstream from the premixing nozzles partition elements for dividing the space along the axis of the combustor or a honeycomb element having air passages in the axial direction, or by providing premixing nozzles composed of cylindrical elements with many holes.

Abstract: A gas turbine combustor in which a part or all of the wall of the combustor disposed within an intake chamber is formed as an acoustic energy absorbing member that can absorb the acoustic energy of a combustion variation generated within the combustor. The acoustic energy absorbing member is constructed of a thin corrugated plate in a circumferential direction, a high-temperature-proof perforated material, or a back plate disposed at the outside of a perforated plate in a radial direction with a distance from the perforated plate. It is also possible to provide a covering member at the outside of the acoustic energy absorbing member in a radial direction, for covering the acoustic energy absorbing member with a distance from the acoustic energy absorbing member. It is preferable that the acoustic energy-absorbing member and/or the covering member are reinforced with a frame that extends in a circumferential direction and/or a longitudinal direction.

Abstract: A gas turbine combustor includes a combustion liner in which a combustion region is formed; and a housing provided for a wall of the combustion liner in a predetermined circumferential region of the combustion liner to form a resonance space between the combustion liner and the housing. The combustion region and the resonance space are connected by a plurality of combustion liner through-holes, and a circumferential length of the housing is longer than a diameter of the combustion liner.

Abstract: A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.