Abstract: A cylinder for combustion comprises a barrel having a cylindrical shape, and an air supply pipe. An insertion opening and a plurality of cooling flow paths are formed in the barrel. Collision region flow paths of the plurality of cooling flow paths each have a collision region circumvention flow path part intersecting with a collision gas axis extending in the direction of the flow of combustion gas moving toward a pipe center axis of the air supply pipe. The collision region circumvention flow path parts have an upstream-side direction component from the collision gas axis along the edge of the insertion opening, and have a downstream-side direction component from the collision gas axis along the edge of the insertion opening. No exit is formed in a portion of the collision region circumvention flow path parts within the range of specified angles about the pipe center axis.

Abstract: A plurality of cooling passages extending in an axial direction are formed in a transition piece so as to be aligned in a circumferential direction and the axial direction. One or more downstream side passages are formed in a downstream side region (Rd) within one circumferential region. One or more upstream side passages are formed in an upstream side region Ru within the circumferential region. The total cross-sectional area per unit circumferential length of the one or more downstream side passages is larger than the total cross-sectional area per unit circumferential length of the one or more upstream side passages.

Abstract: Described herein is a topcoat paint composition having an acrylic resin (A) and a melamine resin (B). The acrylic resin (A), relative to 100 parts by mass thereof, contains 30-40 parts by mass of 2-hydroxyethyl methacrylate, 10-30 parts by mass of styrene and 25 parts by mass or more of 2-ethylhexyl acrylate, and does not contain, relative to 100 parts by mass of the acrylic resin (A), more than 5 parts by mass of caprolactone compound(s) and/or hydroxy group-containing (meth)acrylates constituted of 7 or more carbons. The content of acrylic resin (A), relative to 100 parts by mass of total resin solids of the topcoat paint composition, is 45 parts by mass or more. The content of melamine resin (B), which does not contain complete alkyl ether type melamine resin, relative to the acrylic resin (A), as resin solids ratio, is acrylic resin (A)/melamine resin (B)=50/50 to 80/20.

Abstract: A plurality of cooling passages extending in an axial direction are formed in a transition piece so as to be aligned in a circumferential direction and the axial direction. One or more downstream side passages are formed in a downstream side region (Rd) within one circumferential region. One or more upstream side passages are formed in an upstream side region Ru within the circumferential region. The total cross-sectional area per unit circumferential length of the one or more downstream side passages is larger than the total cross-sectional area per unit circumferential length of the one or more upstream side passages.

Abstract: A measuring jig includes: a base portion; a sensor holding portion disposed so as to protrude from the base portion and configured to hold a sensor; and a first protruding portion protruding from the base portion toward the same side as the sensor holding portion, at a first position different from a sensor position which is a position of a sensor installation surface on which the sensor extends, with respect to a direction orthogonal to the sensor installation surface.

Abstract: A cylinder for a combustor includes a cylindrical member, a first cooling passage defined in the cylindrical member and a second cooling passage defined in the cylindrical member, and a supply port extender. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extender includes a first wall that is disposed between the supply port and the discharge port and extends away from the outer peripheral surface of the cylindrical member and a second wall that is disposed upstream of the supply port and extends away from the outer peripheral surface of the cylindrical member.

Abstract: A combustor including: a transition piece having a cylindrical shape and including an inlet of combustion gas at one end and an outlet of the combustion gas at the other end and configured to allow the combustion gas flowing from the inlet to flow out from the outlet so as to introduce the combustion gas into a turbine; a cooling medium introduction unit introduced with the cooling medium and provided on an outer periphery portion in an outlet side of the transition piece; a cooling medium inlet configured to introduce the cooling medium into the cooling medium introduction unit; and a cooling portion, connected to the cooling medium introduction unit, provided on a portion from the outlet of the transition piece toward the inlet and configured to allow the cooling medium from the cooling medium introduction unit to pass through the outlet toward the inlet.

Abstract: An exhaust system and a gas turbine, in which the exhaust system includes an exhaust casing; an outer diffuser supported inside the exhaust casing; an inner diffuser disposed inside the outer diffuser to form an exhaust gas flow passage between the inner diffuser and the outer diffuser; a strut cover coupled at a first end to the outer diffuser and coupled at a second end to the inner diffuser; and a second cooling air introduction port provided in the exhaust casing, further on the downstream side of the exhaust gas flow passage than the strut cover. Furthermore, a non-perforated partition member having an annular shape is arranged so as to cover the outer side of the outer diffuser and is supported by the exhaust casing to form a cooling air flow passage.

Abstract: Described herein is a topcoat paint composition having an acrylic resin (A) and a melamine resin (B). The acrylic resin (A), relative to 100 parts by mass thereof, contains 30-40 parts by mass of 2-hydroxyethyl methacrylate, 10-30 parts by mass of styrene and 25 parts by mass or more of 2-ethylhexyl acrylate, and does not contain, relative to 100 parts by mass of the acrylic resin (A), more than 5 parts by mass of caprolactone compound(s) and/or hydroxy group-containing (meth)acrylates constituted of 7 or more carbons. The content of acrylic resin (A), relative to 100 parts by mass of total resin solids of the topcoat paint composition, is 45 parts by mass or more. The content of melamine resin (B), which does not contain complete alkyl ether type melamine resin, relative to the acrylic resin (A), as resin solids ratio, is acrylic resin (A)/melamine resin (B)=50/50 to 80/20.

Abstract: A gas turbine combustor comprising a plurality of cooling air passages (27A) through which bled pressurized air flows from downstream of a combustion gas flow toward upstream, the plurality of cooling air passages (27A) being disposed in a wall portion (26) side by side and aligned in a flow direction of a combustion gas; wherein the plurality of cooling air passages (27A) are divided via a passage transition groove portion (33) into upstream cooling air passages (27A1) disposed closer to bled pressurized air inlet holes (30a) and downstream cooling air passages (27A2) disposed closer to bled pressurized air outlet holes (30b), and center lines (C1) of the upstream cooling air passages are non-collinear with center lines (C2) of the downstream cooling air passages.

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 measuring jig includes: a base portion; a sensor holding portion disposed so as to protrude from the base portion and configured to hold a sensor; and a first protruding portion protruding from the base portion toward the same side as the sensor holding portion, at a first position different from a sensor position which is a position of a sensor installation surface on which the sensor extends, with respect to a direction orthogonal to the sensor installation surface.

Abstract: A plurality of cooling passages extending in an axial direction are formed in a transition piece so as to be aligned in a circumferential direction and the axial direction. One or more downstream side passages are formed in a downstream side region (Rd) within one circumferential region. One or more upstream side passages are formed in an upstream side region Ru within the circumferential region. The total cross-sectional area per unit circumferential length of the one or more downstream side passages is larger than the total cross-sectional area per unit circumferential length of the one or more upstream side passages.

Abstract: A combustor including: a transition piece having a cylindrical shape and including an inlet of combustion gas at one end and an outlet of the combustion gas at the other end and configured to allow the combustion gas flowing from the inlet to flow out from the outlet so as to introduce the combustion gas into a turbine; a cooling medium introduction unit introduced with the cooling medium and provided on an outer periphery portion in an outlet side of the transition piece; a cooling medium inlet configured to introduce the cooling medium into the cooling medium introduction unit; and a cooling portion, connected to the cooling medium introduction unit, provided on a portion from the outlet of the transition piece toward the inlet and configured to allow the cooling medium from the cooling medium introduction unit to pass through the outlet toward the inlet.

Abstract: The present invention provides an exhaust system and a gas turbine. The exhaust system includes: an exhaust casing; an outer diffuser supported inside the exhaust casing; an inner diffuser disposed inside the outer diffuser to form an exhaust gas flow passage between the inner diffuser and the outer diffuser; a strut cover coupled at one end to the outer diffuser and coupled at the other end to the inner diffuser; a second cooling air introduction port provided in the exhaust casing, further on the downstream side of the exhaust gas flow passage than the strut cover; a partition member having an annular shape so as to cover the outer side of the outer diffuser and supported by the exhaust casing; and a cooling air flow passage.

Abstract: A cylinder for a combustor provided with a cylindrical member, a first cooling passage and a second cooling passage formed in the cylindrical member, and a supply port extended portion. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extended portion includes a first wall portion disposed between the supply port and the discharge port extending away from the outer peripheral surface of the cylindrical member and a second wall portion disposed upstream of the supply port extending away from the outer peripheral surface of the cylindrical member.

Abstract: A gas turbine combustor comprising a plurality of cooling air passages (27A) through which bled pressurized air flows from downstream of a combustion gas flow toward upstream, the plurality of cooling air passages (27A) being disposed in a wall portion (26) side by side and aligned in a flow direction of a combustion gas; wherein the plurality of cooling air passages (27A) are divided via a passage transition groove portion (33) into upstream cooling air passages (27A1) disposed closer to bled pressurized air inlet holes (30a) and downstream cooling air passages (27A2) disposed closer to bled pressurized air outlet holes (30b), and center lines (C1) of the upstream cooling air passages are non-collinear with center lines (C2) of the downstream cooling air passages.

Abstract: Disclosed herein is a paint composition comprising a carboxyl group containing resin comprising two or more carboxyl groups per molecule, having an acid number of from 100 to 300 mgKOH/g and a weight average molecular weight of from 2,000 to 30,000, obtained by the copolymerization of a carboxyl group containing radically polymerizable monomer and another radically polymerizable monomer, wherein the carboxyl group containing resin comprises 5 to 50 weight percent of structural units based on a lactone compound, based on resin solids; an epoxy group containing resin, comprising two or more epoxy groups per molecule; an ultraviolet absorber; and a light stabilizer having a pKb value of at least 9; wherein the molar ratio of the carboxyl groups of the carboxyl group containing resin to the epoxy groups of the epoxy group containing resin is 3:1 to 1:3.

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: 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.