Abstract: A combustor component according to at least one embodiment of the present invention includes a cylindrical body which internally includes a combustion chamber, and includes a weld part where a plurality of through holes opening to the combustion chamber are formed, and a housing which is disposed on an outer circumferential side of the cylindrical body to cover a part of the weld part, and defines an acoustic damping space communicating with the combustion chamber via at least one of the through holes. The plurality of through holes in the weld part has a formation density which is higher in a first region of the weld part covered with the housing than in a second region of the weld part positioned outside the housing.

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 component according to at least one embodiment of the present invention includes a cylindrical body which internally includes a combustion chamber, and includes a weld part where a plurality of through holes opening to the combustion chamber are formed, and a housing which is disposed on an outer circumferential side of the cylindrical body to cover a part of the weld part, and defines an acoustic damping space communicating with the combustion chamber via at least one of the through holes. The plurality of through holes in the weld part has a formation density which is higher in a first region of the weld part covered with the housing than in a second region of the weld part positioned outside the housing.

Abstract: A gas turbine combustor and a gas turbine; wherein inclined surfaces are provided on inner surfaces of side walls neighboring in a circumferential direction at downstream end portions of transition pieces of combustors, the inclined surfaces being configured to increase a passage area of the transition pieces, a ratio (S/P) is from 0 to 0.2, where (P) is a pitch dimension of first stage vanes, and (S) is a circumferential dimension from an intermediate point between neighboring transition pieces to an upstream end of a first stage vane closest in the circumferential direction; and a ratio (L/P) is from 0.3 to 0.55, where (P) is the pitch dimension, and (L) is an axial dimension from a downstream end of the transition piece to the upstream end of the first stage vane.

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 seal member assembly structure and assembly method, a seal member, and a gas turbine, wherein, in a state where first flange parts provided on a combustor transition piece are fitted into first fitting parts provided in seal members, protruding parts provided on the first flange parts are inserted into recessed parts provided in the first fitting parts.

Abstract: An inkjet printing apparatus for forming images with ink droplets includes the following elements: an inkjet head, a plurality of holders for removably holding a plurality of ink tanks storing inks interchangeable with each other, branch pipes each having one end thereof connected to one of the ink tanks, a mixer provided at the other ends of the branch pipes, a pump for feeding the inks to the mixer, a feed pipe connecting the mixer and the inkjet head, and a controller for controlling ink feeding. The controller makes different a feed rate of the ink from each of the ink tanks.

Abstract: A combustor panel having a plurality of cooling flow paths formed between the outer surface and the inner surface of the combustor panel. The cooling flow paths have inlets that open at the outer surface and introduce a cooling medium into their interior, and outlets that open at the inner surface and discharge the cooling medium flowing through their interior. Among the plurality of cooling flow paths, each of plurality of cooling flow paths extending from a position along the edge of an aperture of the combustor panel forms an aperture-vicinity flow path. Among the plurality of aperture-vicinity flow paths, each of the aperture-vicinity flow paths for which the inlet is formed closer to the aperture than the outlet forms an aperture-side inlet flow path. The number of the aperture-side inlet flow paths is greater than one-half of the all of the aperture-vicinity flow paths.

Abstract: An inkjet printing apparatus for forming images with ink droplets includes the following elements: an inkjet head, a plurality of holders for removably holding a plurality of ink tanks storing inks interchangeable with each other, branch pipes each having one end thereof connected to one of the ink tanks, a mixer provided at the other ends of the branch pipes, a pump for feeding the inks to the mixer, a feed pipe connecting the mixer and the inkjet head, and a controller for controlling ink feeding. The controller makes different a feed rate of the ink from each of the ink tanks.

Abstract: A combustor panel having a plurality of cooling flow paths formed between the outer surface and the inner surface of the combustor panel. The cooling flow paths have inlets that open at the outer surface and introduce a cooling medium into their interior, and outlets that open at the inner surface and discharge the cooling medium flowing through their interior. Among the plurality of cooling flow paths, each of plurality of cooling flow paths extending from a position along the edge of an aperture of the combustor panel forms an aperture-vicinity flow path. Among the plurality of aperture-vicinity flow paths, each of the aperture-vicinity flow paths for which the inlet is formed closer to the aperture than the outlet forms an aperture-side inlet flow path. The number of the aperture-side inlet flow paths is greater than one-half of the all of the aperture-vicinity flow paths.

Abstract: A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket.

Abstract: A seal member assembly structure and assembly method, a seal member, and a gas turbine, wherein, in a state where first flange parts provided on a combustor transition piece are fitted into first fitting parts provided in seal members, protruding parts provided on the first flange parts are inserted into recessed parts provided in the first fitting parts.

Abstract: A gas turbine combustor and a gas turbine; wherein inclined surfaces are provided on inner surfaces of side walls neighboring in a circumferential direction at downstream end portions of transition pieces of combustors, the inclined surfaces being configured to increase a passage area of the transition pieces, a ratio (S/P) is from 0 to 0.2, where (P) is a pitch dimension of first stage vanes, and (S) is a circumferential dimension from an intermediate point between neighboring transition pieces to an upstream end of a first stage vane closest in the circumferential direction; and a ratio (L/P) is from 0.3 to 0.55, where (P) is the pitch dimension, and (L) is an axial dimension from a downstream end of the transition piece to the upstream end of the first stage vane.

Abstract: A cylinder of a combustor includes a cylinder body inside of which combustion gas flows, a jacket plate that covers the cylinder body from the outside and forms a fluid space into which high-pressure fluid flows between an inner peripheral surface of the jacket plate and an outer peripheral surface of the cylinder body, and a rib that connects the cylinder body and the jacket plate. The rib is connected to the cylinder body by a cylinder side end portion on the cylinder body side in a radial direction with respect to an axis of the cylinder body being welded from both sides in an axial direction of the axis. The rib is connected to the jacket plate by a jacket side end portion on the jacket plate side in the radial direction being welded from both sides in the axial direction.

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: Disclosed is an inspecting chart including a reference pattern containing a first line segment group and a second line segment group, a first-side deviation pattern, and a second-side deviation pattern. The first line segment group is formed by a plurality of first line segments printed by a reference printing head at a first given interval. The second line segment is formed by second line segments printed by a printing head on a center between two adjacent first line segments or a center of each of the first line segments, the printing head being spaced away from the reference printing head in the transportation direction of a print medium. The first-side deviation pattern and the second-side deviation pattern are printed with various deviations.

Abstract: A combustor seal structure includes a first recess portion and a second recess portion that are provided on opposing faces in adjacent flange portions of a transition piece; a seal member body disposed across the first recess portion and the second recess portion; a first projection portion and a second projection portion 64 that are provided at each end portion in the width direction of the seal member body and are capable of being in contact with a first seal face of the first recess portion and a second seal face of the second recess portion; a first spring member whose base end portion is connected to one end portion in the width direction of the seal member body and whose distal end portion extends to the other end portion and is capable of being in contact with a second pressing face.

Abstract: Disclosed is an inspecting chart including a reference pattern containing a first line segment group and a second line segment group, a first-side deviation pattern, and a second-side deviation pattern. The first line segment group is formed by a plurality of first line segments printed by a reference printing head at a first given interval. The second line segment is formed by second line segments printed by a printing head on a center between two adjacent first line segments or a center of each of the first line segments, the printing head being spaced away from the reference printing head in the transportation direction of a print medium. The first-side deviation pattern and the second-side deviation pattern are printed with various deviations.

Abstract: A gas turbine combustor is disposed in a casing interior space of a gas turbine. A combustor basket of the combustor is formed into a cylindrical shape by abutting ends of a curved panel member and welding the ends together along a welding line 16. A communication tube is provided for communication between an interior space of the combustor basket and an interior space of a combustor basket of an adjacent combustor. The position of the welding line of the combustor basket coincides with a connection position for connecting the communication tube to the combustor basket. A cooling air hole is disposed in the communication tube or in the combustor basket in the vicinity of the communication tube to introduce cooling air from the casing interior space 9 to the interior of the combustor basket.

Abstract: Disclosed is an inspecting chart including a reference pattern containing a first line segment group and a second line segment group, a first-side deviation pattern, and a second-side deviation pattern. The first line segment group is formed by a plurality of first line segments printed by a reference printing head at a first given interval. The second line segment is formed by second line segments printed by a printing head on a center between two adjacent first line segments or a center of each of the first line segments, the printing head being spaced away from the reference printing head in a the transportation direction of a print medium. The first-side deviation pattern and the second-side deviation pattern are printed with various deviations.