Abstract: The purpose of the invention is to provide a rotor blade support structure, wherein the concentration of stress near the rotor blade groove in which the rotor blade is embedded is limited even as increase in production cost is limited. A rotor blade support structure, in which rotor blades (30) are embedded in rotor blade grooves (10) provided on a rotor disc (1), wherein the rotor blade groove (10) is provided with circular direction grooves (13) that extend more in the circular direction of the rotor disc than upward from the bottom (14), and shaft center direction grooves (15) that are provided on the end faces (1a, 1b) of the rotor disc (1) in the center of the bottom (14) in the circular direction of the rotor disc and that extend towards the rotor disc shaft center.

Abstract: In a disc axis adjusting mechanism in a gas turbine, the gas turbine has an exhaust gas diffuser provided between a casing wall and a bearing case which are connected to a downstream side of a turbine, a plurality of struts provided at intervals in a circumferential direction, and strut covers coupling an outer diffuser and an inner diffuser of the exhaust gas diffuser so as to cover the struts, and the mechanism comprises: a plurality of air introduction holes formed in the casing wall so as to allow the interior and exterior of the wall to communicate with each other; a sensor unit configured to detect a parameter corresponding to the thermal elongation of each of the struts; and a flow rate adjustor configured to adjust the flow rate of air flowing through each of the air introduction holes based on a detection value detected by the sensor unit.

Abstract: A gas turbine includes a combustor chamber that houses a combustor unit configured to include a combustor that burns fuel to generate combustion gas for rotating a rotor, a turbine unit chamber that houses a turbine-unit rotor blade and a disk that rotate upon reception of the combustion gas, a combustor casing that forms the combustor chamber, and a casing that is configured to include the combustor casing in which a divided portion on a surface orthogonal to a rotation axis of the rotor is not formed in the combustor casing, but is formed in a portion on a downstream side of flow of the combustion gas lower than the combustor casing.

Abstract: In a disc axis adjusting mechanism in a gas turbine, the gas turbine has an exhaust gas diffuser provided between a casing wall and a bearing case which are connected to a downstream side of a turbine, a plurality of struts provided at intervals in a circumferential direction, and strut covers coupling an outer diffuser and an inner diffuser of the exhaust gas diffuser so as to cover the struts, and the mechanism comprises: a plurality of air introduction holes formed in the casing wall so as to allow the interior and exterior of the wall to communicate with each other; a sensor unit configured to detect a parameter corresponding to the thermal elongation of each of the struts; and a flow rate adjustor configured to adjust the flow rate of air flowing through each of the air introduction holes based on a detection value detected by the sensor unit.

Abstract: The purpose of the invention is to provide a rotor blade support structure, wherein the concentration of stress near the rotor blade groove in which the rotor blade is embedded is limited even as increase in production cost is limited. A rotor blade support structure, in which rotor blades (30) are embedded in rotor blade grooves (10) provided on a rotor disc (1), wherein the rotor blade groove (10) is provided with circular direction grooves (13) that extend more in the circular direction of the rotor disc than upward from the bottom (14), and shaft center direction grooves (15) that are provided on the end faces (1a, 1b) of the rotor disc (1) in the center of the bottom (14) in the circular direction of the rotor disc and that extend towards the rotor disc shaft center.

Abstract: A gas turbine includes a rotor rotated by combustion gas produced by a combustor that burns fuel, and a casing that is formed by connecting a plurality of casing members divided in plurality, the casing storing the rotor in an inside thereof, and including a second upper-side second vertical inner flange and a third upper-side first vertical inner flange for connecting a second upper casing member with a third upper casing member different from the second upper casing member among the casing members at the inside.

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: A gas turbine includes a combustor chamber that houses a combustor unit configured to include a combustor that burns fuel to generate combustion gas for rotating a rotor, a turbine unit chamber that houses a turbine-unit rotor blade and a disk that rotate upon reception of the combustion gas, a combustor casing that forms the combustor chamber, and a casing that is configured to include the combustor casing in which a divided portion on a surface orthogonal to a rotation axis of the rotor is not formed in the combustor casing, but is formed in a portion on a downstream side of flow of the combustion gas lower than the combustor casing.

Abstract: A gas turbine includes a rotor rotated by combustion gas produced by a combustor that burns fuel, and a casing that is formed by connecting a plurality of casing members divided in plurality, the casing storing the rotor in an inside thereof, and including a second upper-side second vertical inner flange and a third upper-side first vertical inner flange for connecting a second upper casing member with a third upper casing member different from the second upper casing member among the casing members at the inside.

Abstract: In a gas turbine combustor, a cavity (49) with which a plurality of first air passages (66) communicates is formed by covering with a cover (62) a concave portion (65) of a top hat main body (61) in which the first air passages (66) are formed along the circumferential direction of the top hat main body (61), a plurality of second fuel passages (67) that communicates with the first fuel passages are formed by connecting an inner ring (63) and an outer ring (64) to the top hat main body (61) and by connecting the inner ring (63) and the outer ring (64) to each other, a peg (52) is fixed on the inner ring (63) to communicate with the second fuel passage (67) through a third air passage (68), and thin wall portions (63b, 64b) that serve as a thermal elongation absorbing unit by which thermal elongation is absorbed are provided on the inner ring (63) and the outer ring (64).