Abstract: Provided is a laminate that is excellent in heat sealing properties and is suitable for reuse. The laminate includes: a first layer having a melting point of Tm1 and containing a first polyethylene alone as a resin; and a second layer having a melting point of Tm2 and containing a second polyethylene alone as a resin, where: the first layer and the second layer are disposed respectively as outermost surfaces of the laminate; and Tm1?Tm2?24.0° C. is satisfied.

Abstract: Provided is a laminate that is excellent in heat sealing properties and is suitable for reuse. The laminate includes: a first layer having a melting point of Tm1 and containing a first polyethylene alone as a resin; and a second layer having a melting point of Tm2 and containing a second polyethylene alone as a resin, where: the first layer and the second layer are disposed respectively as outermost surfaces of the laminate; and Tm1?Tm2?24.0° C. is satisfied.

Abstract: Provided are a method for three-dimensionally molding a film, a method for manufacturing a film molded body, and a film molded body that make it possible to easily perform three-dimensional molding of an inner film portion while achieving a reduction in processing time and a decrease in energy consumption and without requiring a design change to the existing equipment. A method for three-dimensionally molding a film, the method including performing cold compression molding in a thickness direction on a film overlapping section in which at least one inner film portion including a first layer and a second layer having an elongation smaller than that of the first layer is arranged between two outer film portions in a non-fixed state with respect to the outer film portions, thereby causing the inner film portion to protrude toward the second layer side at the film overlapping section.

Abstract: A turbine rotor blade includes an airfoil portion having an airfoil defined by a pressure surface and a suction surface; and a squealer rib on a tip surface of the turbine rotor blade, the squealer rib extending from a leading-edge side (toward a trailing-edge side. The squealer rib has a ridge extending in an extending direction of the squealer rib. The turbine rotor blade is configured to provide a clearance between the tip surface of the turbine rotor blade and an inner wall surface of a casing of a turbine such that the inner wall surface of the casing of the turbine faces the tip surface of the turbine rotor blade and the clearance has a local minimum value on the ridge. The clearance is greater than the local minimum value at both sides of the ridge in a width direction of the squealer rib.

Abstract: A gas turbine provided with an air bleeder tube (1) that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharged the bled air into a cylindrical exhaust duct (20), wherein the air bleeder tube (1) is disposed at a portion that does not obstruct the flow of the main flow of combustion gas.

Abstract: A decorative laminate film including an inner film and an outer film, and at least a part of a character and/or a figure is formed as a protruded portion protruding toward the outer film. A print layer of a high-brightness ink and/or a foamed film is interposed between the inner film and the outer film, and at least a part of the character and/or the figure has a metallic luster derived from the print layer of the high-brightness ink or a pearly luster derived from the foamed film. The character and/or the figure is distinguished from at least a part of the remaining region in at least one of hue, brightness, chroma and gloss, thereby providing a decorative laminate film, which is imparted by the print design and a protruded portion having a metallic luster and/or a pearly luster, without impairing its function as a packaging material.

Abstract: A rotary machine includes turbine moving blades (50); a casing (10) covering the turbine moving blades (50) so as to define a gap at an outer circumferential side of the turbine moving blades; a leaf seal (70) having a seal body (71) that is disposed in the gap so as to protrude radially inward from the casing (10) and is capable of coming into contact with the turbine moving blades (50), and a high-pressure-side plate member (73) that is disposed along a face facing a high pressure side of the seal body (71); and a swirling flow inhibitor (80) that is provided on the high pressure side of the leaf seal (70) in the gap and inhibits a swirl flow flowing through the gap in a circumferential direction.

Abstract: A turbine rotor blade (26) for a turbine includes an airfoil portion (30) having an airfoil formed by a pressure surface (31) and a suction surface (32); and at least one squealer rib (40, 42, 44) disposed on a tip surface (35) of the turbine rotor blade so as to extend from a leading-edge side (33) toward a trailing-edge side (34). At least one (42) of the at least one squealer rib has a ridge (43) extending in an extending direction of the squealer rib. A clearance (100) between the tip surface and an inner wall surface of a casing of the turbine, the inner wall surface facing the tip surface, has a local minimum value on the ridge. The clearance is greater than the local minimum value at both sides of the ridge in a width direction of the squealer rib.

Abstract: A gas turbine provided with an air bleeder tube (1) that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharged the bled air into a cylindrical exhaust duct (20), wherein the air bleeder tube (1) is disposed at a portion that does not obstruct the flow of the main flow of combustion gas.

Abstract: A gas turbine provided with an air bleeder tube (1) that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharged the bled air into a cylindrical exhaust duct (20), wherein the air bleeder tube (1) is disposed at a portion that does not obstruct the flow of the main flow of combustion gas.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a plurality of positions in a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit injects a mixed fuel prepared by mixing water and the liquid fuel evenly from the liquid fuel injecting hole to the vane pressure surface of the swirler vane.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a circumferential direction on an external circumferential surface of the fuel nozzle, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit includes a multi-purpose injecting hole that is arranged on the vane pressure surface of each of the swirler vanes, and from which a gas fuel is injected during gas combustion, and water is injected to the vane pressure surface of the swirler vane during combustion of the liquid fuel.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream so as to swirl air flowing in the air passage from the upstream to the downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane surface of each of the swirler vanes, and a cooling unit that cools a part of the vane surface on which the liquid fuel hits. The cooling unit includes a water cooling circuit formed inside the swirler vane.

Abstract: A centrifugal fluid machine includes an impeller (4) that has a front shroud (41) arranged on one side in an axial direction, a rear shroud (42) arranged on the other side in the axial direction, and a plurality of blades (43) provided side by side in a circumferential direction between the front shroud and the rear shroud and is rotatably supported within a casing (2); a suction passage (2A) that allows a fluid to be sucked therethrough in the axial direction toward the impeller with the rotation of the impeller; a discharge passage (2B) that allows a fluid delivered under pressure by the impeller with the rotation of the impeller to be discharged in a direction intersecting the axial direction of the impeller; and a first flow path (5A) that communicates with the discharge passage, leads to the suction passage through a gap between the casing and the rear shroud, and an opening (5Aa) that opens toward the downstream side of the suction passage in a suction direction of a fluid.

Abstract: A rotary machine includes turbine moving blades (50); a casing (10) covering the turbine moving blades (50) so as to define a gap at an outer circumference side of the turbine moving blades; a leaf seal (70) having a seal body (71) that is disposed in the gap so as to protrude radially inward from the casing (10) and is capable of coming into contact with the turbine moving blades (50), and a high-pressure-side plate member (73) that is disposed along a face facing a high pressure side of the seal body (71); and a swirling flow inhibitor (80) that is provided on the high pressure side of the leaf seal (70) in the gap and inhibits a swirl flow flowing through the gap in a circumferential direction.

Abstract: A centrifugal fluid machine includes an impeller (4) that has a front shroud (41) arranged on one side in an axial direction, a rear shroud (42) arranged on the other side in the axial direction, and a plurality of blades (43) provided side by side in a circumferential direction between the front shroud and the rear shroud and is rotatably supported within a casing (2); a suction passage (2A) that allows a fluid to be sucked therethrough in the axial direction toward the impeller with the rotation of the impeller; a discharge passage (2B) that allows a fluid delivered under pressure by the impeller with the rotation of the impeller to be discharged in a direction intersecting the axial direction of the impeller; and a first flow path (5A) that communicates with the discharge passage, leads to the suction passage through a gap between the casing and the rear shroud, and an opening (5Aa) that opens toward the downstream side of the suction passage in a suction direction of a fluid.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a circumferential direction on an external circumferential surface of the fuel nozzle, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit includes a multi-purpose injecting hole that is arranged on the vane pressure surface of each of the swirler vanes, and from which a gas fuel is injected during gas combustion, and water is injected to the vane pressure surface of the swirler vane during combustion of the liquid fuel.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a plurality of positions in a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit injects a mixed fuel prepared by mixing water and the liquid fuel evenly from the liquid fuel injecting hole to the vane pressure surface of the swirler vane.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream so as to swirl air flowing in the air passage from the upstream to the downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane surface of each of the swirler vanes, and a cooling unit that cools a part of the vane surface on which the liquid fuel hits. The cooling unit includes a water cooling circuit formed inside the swirler vane.

Abstract: A combustion burner 10A according to one embodiment of the present invention includes: a fuel nozzle 110; a burner tube 120 forming the air passage 111 between the burner tube 120 and the fuel nozzle 110; swirler vanes (swirler vanes) 130 arranged in a plurality of positions in the circumferential direction on the external circumferential surface of the fuel nozzle 110, each extending along the axial direction of the fuel nozzle 110, and gradually curving from upstream toward downstream; and a liquid fuel injecting hole 133A from which a liquid fuel is injected to a surface of each of the swirler vanes 130. The combustion burner 10A also includes multi-purpose injecting holes 11-1 to 11-3 as a cooling unit that cools a part of a vane pressure surface 132a of the swirler vane 130 on which the liquid fuel LF hits.