Abstract: A gas turbine equipped with a compressor, a combustion chamber and a turbine is further equipped with: a pressurizing device for taking a portion of the compressed air compressed by the compressor, and pressurizing the compressed air; a combustion chamber cooling line for cooling the combustion chamber using the pressurized compressed air; a temperature regulating line for regulating the temperature of a stationary member of a blade ring or the like of a turbine by using the pressurized compressed air; a combustion chamber supply line through which the compressed air flows from the pressurizing device to the combustion chamber cooling line; a turbine supply line through which the compressed air flows from the pressurizing device to the temperature regulating line; a heater for heating the compressed air, provided in the turbine supply line; and a control device capable of controlling the heater.

Abstract: A single-liquid type paint composition comprises: a hydroxyl group-containing polyester resin (A) of which the weight average molecular weight is from 1,500 to 8,000, the acid value is from 0 to 50 mgKOH/g, the hydroxyl group value is from 100 to 180 mgKOH/g and the glass transition temperature is from ?30 to 0° C. and a crosslinking agent (B) which reacts with hydroxyl groups, wherein the (A) component has been obtained by reacting a polybasic acid (a), a polyhydric alcohol (b) and at least one type of component (c) having at least six carbon atoms selected from among the saturated mono-carboxylic acids, saturated mono-alcohols, saturated glycidyl ethers and saturated glycidyl esters where the proportion by mass of the (c) component is from 20 to 60 mass % with respect to the sum of the solid fraction masses of the (a) to (c) components.

Abstract: A transition piece of a combustor which is sustainable even under conditions of more severe thermal environments is provided in the present invention. A transition piece of a combustor is provided with a cylindrical trunk main body, a cylindrical exit trunk part which is joined to the downstream end of the trunk main body and which cooperates with the trunk main body to constitute a trunk part, and an inner flange which extends from the downstream end part of the exit trunk part toward the outer periphery side of the exit trunk part. The exit trunk part and the inner flange are of an one-piece product. On the exit trunk part, there is formed a groove, and there is formed a cooling fluid passage which opens at the groove.

Abstract: An acoustic damper is fixed to a vibration source to be provided along an outer surface of the vibration source, forms a passage that takes in air vibration generated by the vibration source, and is provided with an acoustic portion having a partition member closing the downstream side of the passage with respect to the propagation of the air vibration to serve as resistance against the air vibration, in which the acoustic portion allows air vibration to propagate in a reverse direction, and has partition members arranged so as to serve as resistance against the air vibration in respective directions. This allows to prevent from generating stress due to pressure fluctuation caused when reducing vibration, and to achieve a relatively compact size.

Abstract: A plate-like-object manufacturing method, plate-like objects, a gas-turbine combustor, and a gas turbine, in which degradation in the cooling performance can be suppressed, the time required for manufacturing a gas-turbine combustor can be shortened, and deterioration of the working environment can be prevented are provided. A plate-like-object manufacturing method includes a step of forming a plate-like object by stacking a plurality of plates and arranging a plurality of channels, through which a cooling medium flows, side-by-side between the plurality of plates; and a step of arranging a plurality of the plate-like objects side-by-side in a direction in which the channels are arranged, butting the plurality of plate-like objects against each other, and performing welding at an abutment section. The channels adjacent to the abutment section extend along the abutment section and have a greater dimension in the direction in which the channels are arranged, as compared with that of other channels.

Abstract: An object is to provide a low cost gas turbine combustor. The gas turbine combustor has a plurality of main nozzles annularly supported on a nozzle pipe base (11), and the main nozzles each have an oil fuel path for supplying oil fuel and a gas fuel path for supplying gas fuel. A plurality of the oil fuel paths are provided to penetrate the nozzle pipe base (11), and a plurality of lengths of upright piping (21) are provided to be connected to the oil fuel paths, respectively, and be erected on the nozzle pipe base (11). A plurality of lengths of connection piping (22) for interconnecting the lengths of the upright piping (21) in a polygonal shape at a minimum distance are provided outside the nozzle pipe base (11). An oil fuel supply section (14) is connected to one of the lengths of the connection piping (22) to distribute oil fuel to each of the oil fuel paths.

Abstract: Disclosed herein is a clear paint composition, comprising (A) an acrylic copolymer comprising from 35 to 50 wt % ?-caprolactone structural units, based on the resin solid fraction, and wherein the hydroxyl number is from 200 to 340 mgKOH/g and the weight average molecular weight is from 5,000 to 15,000 and (B) a non-yellowing type polyisocyanate compound, wherein the isocyanate group of the (B) component is included in a proportion of from 0.5 to 2 equivalents per 1 equivalent of hydroxyl group of the (A) component, wherein the Young's modulus of the hardened paint film obtained from said paint composition is not more than 1.5 Pa, wherein the molecular weight of intercrosslinking of the cured coating film (Mc) is not more than 350 g/mol, and wherein the glass transition temperature (Tg) of the hardened paint film is at least 65° C.

Abstract: An acoustic damper is fixed to a vibration source to be provided along an outer surface of the vibration source, forms a passage that takes in air vibration generated by the vibration source, and is provided with an acoustic portion having a partition member closing the downstream side of the passage with respect to the propagation of the air vibration to serve as resistance against the air vibration, in which the acoustic portion allows air vibration to propagate in a reverse direction, and has partition members arranged so as to serve as resistance against the air vibration in respective directions. This allows to prevent from generating stress due to pressure fluctuation caused when reducing vibration, and to achieve a relatively compact size.

Abstract: A low cost gas turbine combustor has main nozzles having a cylindrical central tube using an interior as an oil fuel path, a cylindrical outer tube disposed on an outermost periphery of the main nozzle, and a support tube disposed between the central tube and the outer tube, the central tube, the outer tube and the support tube each being formed independently. The support tube has such an internal diameter as to form a clearance becoming an insulating air layer between the support tube and an outer periphery of the central tube, and includes supporting portions formed on an axially upstream side and radially contacting an inner periphery of the outer tube groove portions formed along an axial direction between the supporting portions, and a cylindrical portion formed on an axially downstream side and having an external diameter equal to or smaller than an external diameter of the groove portions.

Abstract: In a cooling structure for a recovery-type air-cooled gas turbine combustor having a recovery-type air-cooling structure that bleeds, upstream of the combustor, and pressurizes compressed air supplied from a compressor, that uses the bled and pressurized air to cool a wall, and that recovers and reuses the bled and pressurized air as combustion air for burning fuel in the combustor together with a main flow of the compressed air, wall cooling in which cooling air is supplied to cooling air passages formed in the wall of the combustor to perform cooling involves a downstream wall region, closer to a turbine, that is cooled using the bled and pressurized air as the cooling air and an upstream wall region, closer to a burner, that is cooled using, as the cooling air, bled compressed air bled from a main flow of the compressed air through a housing inner space.

Abstract: A transition piece of a combustor which is sustainable even under conditions of more severe thermal environments is provided in the present invention. A transition piece of a combustor is provided with a cylindrical trunk main body, a cylindrical exit trunk part which is joined to the downstream end of the trunk main body and which cooperates with the trunk main body to constitute a trunk part, and an inner flange which extends from the downstream end part of the exit trunk part toward the outer periphery side of the exit trunk part. The exit trunk part and the inner flange are of an one-piece product. On the exit trunk part, there is formed a groove, and there is formed a cooling fluid passage which opens at the groove.

Abstract: In a gas turbine combustor, a cavity with which a plurality of first air passages communicates is formed by covering with a cover a concave portion of a top hat main body in which the first air passages are formed along the circumferential direction of the top hat main body, a plurality of second fuel passages that communicates with the first fuel passages are formed by connecting an inner ring and an outer ring to the top hat main body and by connecting the inner ring and the outer ring to each other, a peg is fixed on the inner ring to communicate with the second fuel passage through a third air passage, and thin wall portions that serve as a thermal elongation absorbing unit by which thermal elongation is absorbed are provided on the inner ring and the outer ring.

Abstract: Disclosed herein is a paint composition comprising a hydroxyl group containing resin (A), comprising structural units based on 2,2-dimethylolalkanoic acid, having a hydroxyl group value of from 200 to 400 mgKOH/g, and comprising less than 25 weight % in the resin solid fraction of structural units based on a lactone compound; a hydroxyl group containing resin (B), having a hydroxyl group value from 50 to 200 mgKOH/g, and comprising from 25 to 75 weight % in the resin solid fraction of structural units based on a lactone compound; and a crosslinking agent (C) comprising at least two OH-reactive functional groups per molecule; wherein the resin solid fraction weight ratio (A)/(B) of the hydroxyl group containing resin (A) and the hydroxyl group containing resin (B) is from 90/10 to 10/90.

Abstract: Disclosed herein is a heat-hardenable paint composition comprising a base resin, wherein the base resin comprises (A) a lactone modified resin comprising hydroxyl groups, wherein 20 to 70 weight percent of the structural units are based on the lactone compound, and the hydroxyl group value is from 50 to 400 mgKOH/g, and (B) an acrylic resin comprising hydroxyl groups and cyclic structures, wherein 10 to 80 weight percent of structural units are based on a radically polymerizable monomer comprising a cyclic structure, the hydroxyl group value is from 50 to 150 mgKOH/g, and the crosslinking resin is an isocyanate compound, wherein the weight ratio of the solid fractions of (A):(B) in the base resin is from 95:5 to 20:80.

Abstract: A plate-like-object manufacturing method, plate-like objects, a gas-turbine combustor, and a gas turbine, in which degradation in the cooling performance can be suppressed, the time required for manufacturing a gas-turbine combustor can be shortened, and deterioration of the working environment can be prevented are provided. A plate-like-object manufacturing method includes a step of forming a plate-like object by stacking a plurality of plates and arranging a plurality of channels, through which a cooling medium flows, side-by-side between the plurality of plates; and a step of arranging a plurality of the plate-like objects side-by-side in a direction in which the channels are arranged, butting the plurality of plate-like objects against each other, and performing welding at an abutment section. The channels adjacent to the abutment section extend along the abutment section and have a greater dimension in the direction in which the channels are arranged, as compared with that of other channels.

Abstract: An object of the present invention is to provide a gas turbine combustor with improved fatigue resistance of a combustor. It is possible to intentionally reduce a stiffness of each of flanges of upper and lower walls of an end portion (outlet) of the tail pipe of the gas turbine combustor. It is possible to reduce a stiff difference between the upper and lower walls of the end portion (outlet) of the tail pipe section and side walls. Thus, it is possible to reduce compulsion deformation caused due to thermal stress generated in the end portion (outlet) of the tail pipe section on the operation of the conventional gas turbine combustor, and to reduce high stress easy to generate in the side plate. As a result, the gas turbine combustor with high fatigue resistance can be realized.

Abstract: Disclosed herein is a paint composition, comprising a hydroxyl group containing resin (A), having a hydroxyl group value of from 200 to 400 mgKOH/g, and comprising in a resin solid fraction less than 25 weight % of structural units based on a lactone compound, a hydroxyl group containing resin (B), having a hydroxyl group value of from 50 to 200 mgKOH/g, and comprising in the resin solid fraction from 25 to 75 weight % of structural units based on a lactone compound, and a crosslinking agent (C) comprising at least one functional group which reacts with hydroxyl groups, wherein the proportions by weight (A)/(B) of the hydroxyl group containing resin (A) and the hydroxyl group containing resin (B), based on the resin solid fraction, are from 90/10 to 10/90.

Abstract: An object is to provide a low cost gas turbine combustor. The gas turbine combustor comprises main nozzles (3) each having a cylindrical central tube (4) using an interior thereof as an oil fuel path (6) through which oil fuel flows, a cylindrical outer tube (5) disposed on an outermost periphery of the main nozzle (3), and a support tube (8) disposed between the central tube (4) and the outer tube (5), the central tube (4), the outer tube (5) and the support tube (8) each being formed independently.

Abstract: An object is to provide a low cost gas turbine combustor. The gas turbine combustor has a plurality of main nozzles annularly supported on a nozzle pipe base (11), and the main nozzles each have an oil fuel path for supplying oil fuel and a gas fuel path for supplying gas fuel. A plurality of the oil fuel paths are provided to penetrate the nozzle pipe base (11), and a plurality of lengths of upright piping (21) are provided to be connected to the oil fuel paths, respectively, and be erected on the nozzle pipe base (11). A plurality of lengths of connection piping (22) for interconnecting the lengths of the upright piping (21) in a polygonal shape at a minimum distance are provided outside the nozzle pipe base (11). An oil fuel supply section (14) is connected to one of the lengths of the connection piping (22) to distribute oil fuel to each of the oil fuel paths.

Abstract: Disclosed herein is a heat-hardenable paint composition comprising a base resin, wherein the base resin comprises (A) a lactone modified resin comprising hydroxyl groups, wherein 20 to 70 weight percent of the structural units are based on the lactone compound, and the hydroxyl group value is from 50 to 400 mgKOH/g, and (B) an acrylic resin comprising hydroxyl groups and cyclic structures, wherein 10 to 80 weight percent of structural units are based on a radically polymerizable monomer comprising a cyclic structure, the hydroxyl group value is from 50 to 150 mgKOH/g, and the crosslinking resin is an isocyanate compound, wherein the weight ratio of the solid fractions of (A):(B) in the base resin is from 95:5 to 20:80.