Abstract: A device that reduces human energy loss in the breathing process, without requiring external energy such as electricity. The device transfers motion, elastic or heat energy by conveying air volume and pressure between the exhaling and inhaling phases in the breathing process in order to adjust the air pressure or temperature in these phases so as to improve air perfusion or the body's thermal homeostatic conditions as required, in addition to reducing the air resistance in masks or respirators used for protection against contaminants. The invention pertains to the field of healthcare. The invention comprises inhalation and exhalation chambers that are associated with air pumps, besides having elastic energy accumulation walls to minimize air flow resistance.

Abstract: A cooling structure of a turbine airfoil cools a turbine airfoil (10) exposed to hot gas (1), using cooling air (2) of a temperature lower than that of the hot gas. The turbine airfoil (10) includes an external surface (11), an internal surface (12) opposite to the external surface, a plurality of film-cooling holes (13) blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections (14) integrally formed with the internal surface and protruding inwardly from the internal surface. The turbine airfoil further includes a hollow cylindrical insert (20) which is positioned inside the internal surface of the turbine airfoil and to which the cooling air is supplied. The insert has a plurality of impingement holes (21) for impingement-cooling the internal surface (12).

Abstract: It has a flat impingement hole (2) of which the opening width (D1) in the flow direction of a crossflow (F) in the gap between a cooling target (10) and an opposing member (20) is set greater than the opening width (D2) in a direction orthogonal with the flow direction of the crossflow F. Accordingly, the cooling efficiency is further improved by the impingement cooling mechanism.

Abstract: In this cooling structure, a cooling flow path, which is meandering around a flow direction of a high temperature combustion gas, is provided in a structural body. The cooling flow path has an inflow path for a cooling air formed inside of the structural body; at least one straight flow path provided with intervals with respect to an axial line; and a turning flow path for communicating the end portions of the inflow path with the straight flow path or communicating with the end portions of the straight flow paths one after another.

Abstract: An impingement cooled structure includes a plurality of shroud members disposed in a circumferential direction to constitute a ring-shaped shroud surrounding a hot gas stream, and a shroud cover mounted on radial outside faces of the shroud members to form a cavity therebetween. The shroud cover has a first impingement cooling hole which communicates with the cavity and allows cooling air to be jetted to an inside thereof so as to cool an inner surface of the cavity by impingement. The shroud members each has a hole fin. The hole fin divides the cavity into a plurality of sub-cavities. Further, the hole fin has a second impingement cooling hole which allows the cooling air having flowed through the first impingement cooling hole to be jetted obliquely toward a bottom surface of the sub-cavity adjacent thereto.

Abstract: A cooling structure of a turbine airfoil cools a turbine airfoil (10) exposed to hot gas (1), using cooling air (2) of a temperature lower than that of the hot gas. The turbine airfoil (10) includes an external surface (11), an internal surface (12) opposite to the external surface, a plurality of film-cooling holes (13) blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections (14) integrally formed with the internal surface and protruding inwardly from the internal surface. The turbine airfoil further includes a hollow cylindrical insert (20) which is positioned inside the internal surface of the turbine airfoil and to which the cooling air is supplied. The insert has a plurality of impingement holes (21) for impingement-cooling the internal surface (12).

Abstract: A steam valve in accordance with the present invention is the steam valve that houses a first valve device 21 composed of a valve seat, a valve body, a valve rod, and a driving device, and a second valve device 22 composed of the valve seat, the valve body, the valve rod, and the driving device, combined with each other in the valve casing 23, and a closing portion 41 to block a part of a main steam flow flowing from outside to inside of a strainer is formed in the strainer 27 that is housed in the valve casing 23 and that surrounds the valve body 29 of the first valve device. According to the above described configuration, the steam valve that is aimed to further decrease a pressure loss can be provided by effectively controlling the steam flow in the strainer housed in the valve casing.

Abstract: In this cooling structure, a cooling flow path, which is meandering around a flow direction of a high temperature combustion gas, is provided in a structural body. The cooling flow path has an inflow path for a cooling air formed inside of the structural body; at least one straight flow path provided with intervals with respect to an axial line; and a turning flow path for communicating the end portions of the inflow path with the straight flow path or communicating with the end portions of the straight flow paths one after another.

Abstract: An impingement cooled structure includes a plurality of shroud members disposed in a circumferential direction to constitute a ring-shaped shroud surrounding a hot gas stream, and a shroud cover mounted on radial outside faces of the shroud members to form a cavity therebetween. The shroud cover has a first impingement cooling hole which communicates with the cavity and allows cooling air to be jetted to an inside thereof so as to cool an inner surface of the cavity by impingement. The shroud members each has a hole fin. The hole fin divides the cavity into a plurality of sub-cavities. Further, the hole fin has a second impingement cooling hole which allows the cooling air having flowed through the first impingement cooling hole to be jetted obliquely toward a bottom surface of the sub-cavity adjacent thereto.

Abstract: A steam valve in accordance with the present invention is the steam valve that houses a first valve device 21 composed of a valve seat, a valve body, a valve rod, and a driving device, and a second valve device 22 composed of the valve seat, the valve body, the valve rod, and the driving device, combined with each other in the valve casing 23, and a closing portion 41 to block a part of a main steam flow flowing from outside to inside of a strainer is formed in the strainer 27 that is housed in the valve casing 23 and that surrounds the valve body 29 of the first valve device. According to the above described configuration, the steam valve that is aimed to further decrease a pressure loss can be provided by effectively controlling the steam flow in the strainer housed in the valve casing.

Abstract: A gas turbine plant comprises an air compressor, a gas turbine combustor and a gas turbine, which are operatively connected in series. In the gas turbine plant, an air compressor shaft is accommodated in the air compressor and composed of discs piled up along an axial direction of the air compressor shaft, a gas turbine shaft is accommodated in the gas turbine and composed of discs piled up along an axial direction of the gas turbine shaft, and an intermediate shaft is interposed between the air compressor shaft and the gas turbine shaft. At least one of the discs of the air compressor shaft and the discs of the gas turbine shaft are provided with bulged portions each having approximately a hanging bell shape or trapezoidal shape.

Abstract: A cooling apparatus is provided for a gas turbine moving blade and also to a gas turbine equipped with the cooling apparatus. The device is applicable to an electric power plant or the like, and more particularly, to a closed-loop cooling type cooling apparatus for a moving blade which achieves higher cooling efficiency by supplying in parallel a cooling medium from the inside of the turbine rotor to respective moving blades forming a plurality of stages and recovering the cooling medium which has been used for cooling so as to achieve higher energy efficiency.

Abstract: A combined cycle power plant comprises a gas turbine system and a steam cycle system having a steam turbine to be driven by the steam generated by the waste heat of the exhaust gas of the gas turbine system, wherein the steam from the steam cycle system flows through a gas turbine cooling system of the gas turbine to cool the gas turbine blades and other elements of the gas turbine system to be cooled and the waste heat of the gas turbine system is effectively collected. The gas turbine cooling system is supplied selectively with bleed air from the compressor of the gas turbine or the steam provided from another steam cycle system in order to ensure a sufficient coolant supply at the time of starting and stopping the plant and during the operation with a partial load.

Abstract: A gas turbine is equipped with a moving blade cooling apparatus arranged in association with a turbine rotor in which a plurality of discs are mounted, a plurality of moving blades are mounted each to an outer peripheral portion of each of the discs and a plurality of spacers are also disposed in spaces between the respective discs at portions corresponding to a location of stationary blades and in which the moving blades are formed each with a cooling medium flowing passage and the discs and the spacers are arranged with spaces therebetween for passing a cooling medium in a radial direction of the rotor. A closed-loop cooling unit is thus formed for supplying the cooling medium to the cooling medium flowing passage formed in the moving blade and recovering the same therefrom.

Abstract: A combined cycle power plant comprises a gas turbine system and a steam cycle system having a steam turbine to be driven by the steam generated by the waste heat of the exhaust gas of the gas turbine system, wherein the steam from the steam cycle system flows through a gas turbine cooling system of the gas turbine to cool the gas turbine blades and other elements of the gas turbine system to be cooled and the waste heat of the gas turbine system is effectively collected. The gas turbine cooling system has two or more than two cooling ducts formed in two or more than two elements of the gas turbine system to be cooled such as the gas turbine blades and the combustor of the gas turbine system so that steam is made to flow through the cooling ducts of these two or more than two elements to be cooled to effectively and maximally exploit the cooling potential and the waste heat collecting potential of the steam and hence improve the overall thermal efficiency of the plant.

Abstract: A combined cycle power plant comprises a gas turbine system and a steam cycle system having a steam turbine to be driven by the steam generated by the waste heat of the exhaust gas of the gas turbine system, wherein the steam from the steam cycle system flows through a gas turbine cooling system of the gas turbine to cool the gas turbine blades and other elements of the gas turbine system to be cooled and the waste heat of the gas turbine system is effectively collected. The gas turbine cooling system has two or more than two coolooling ducts formed in two or more than two elements of the gas turbine system to be cooled such as the gas turbine blades and the combustor of the gas turbine system so that steam is made to flow through the cooling ducts of these two or more than two elements to be cooled to effectively and maximally exploit the cooling potential and the waste heat collecting potential of the steam and hence improve the overall thermal efficiency of the plant.

Abstract: A combined cycle power plant comprises a gas turbine system and a steam cycle system having a steam turbine to be driven by the steam generated by the waste heat of the exhaust gas of the gas turbine system, wherein the steam from the steam cycle system flows through a gas turbine cooling system of the gas turbine to cool the gas turbine blades and other elements of the gas turbine system to be cooled and the waste heat of the gas turbine system is effectively collected. The gas turbine cooling system has two or more than two cooling ducts formed in two or more than two elements of the gas turbine system to be cooled such as the gas turbine blades and the combustor of the gas turbine system so that steam is made to flow through the cooling ducts of these two or more than two elements to be cooled to effectively and maximally exploit the cooling potential and the waste heat collecting potential of the steam and hence improve the overall thermal efficiency of the plant.

Abstract: A turbine blade performs internal cooling by a cooling gas flowing through internal cooling flow passages and FCFC cooling by a cooling gas jetted out through film holes arranged on the substantially whole area of the blade surface. The film holes are arranged in rows extending in the span direction at predetermined pitches in the chord direction. The dimensions of the elements of the turbine blade are determined by a mathematical formula 5.ltoreq.L/N.multidot.D.ltoreq.50, where L is the length of any interval of the surface of the cooled turbine blade, N is the number of rows of the film holes in the interval and D is an average diameter of the film holes in the interval. With this arrangement, the maximum cooling efficiency at a small amount of cooling gas flow is attained, and both the quantity of heat per unit area of the blade surface transmitted from the main flow gas to the blade surface and the thermal stresses are reduced.

Abstract: A cooling flow passage assembly consisting of pressure side cooling flow passages extending in a span direction and suction side cooling flow passages extending in the span direction and serially connected to the pressure side cooling flow passages is formed in a turbine blade. A cooling medium flows through the pressure side cooling flow passages in the direction toward the tip portion and through the suction side cooling flow passages in the direction toward the root. Cooling effect is improved by a Coriolis force. The number of the suction side cooling flow passages is larger than the number of the pressure side cooling flow passages. At least one of the suction side cooling flow passages forms at least one most downstream cooling flow passage. The cooling medium flows through the most downstream cooling flow passage and is exhausted outside of the turbine blade through nozzles, whereby the flow of the cooling medium through the most downstream cooling flow passage is speeded up.

Abstract: A blade of a gas turbine includes a main body having a dovetail portion and a blade portion extending from the dovetail portion. A cooling air passage for flowing a cooling air is formed in the main body to cool the blade portion. The passage includes a cooling air inlet port open to the dovetail portion and an outlet port open to an extended tip of the blade portion. A first passage portion extends from the inlet port to the portion close to the extended tip along a leading edge of the blade portion. A final passage portion extends from the dovetail portion to the outlet port. The flow sectional area of the final passage portion is gradually decreased from the dovetail portion toward the outlet port. The final passage portion communicates with a number of film cooling holes which are open to the suction side surface of the blade portion.