Abstract: In a burner of an embodiment, a torch part includes: a torch combustor liner that is provided in a torch part casing and burns a fuel and an oxidant; a torch fuel supply part that supplies a fuel; a torch oxidant supply part that supplies an oxidant; an ignition device that ignites a fuel-air mixture; and a combustion gas pipe that is arranged at the center of the torch part and leads a combustion gas in the torch combustor liner to one end side of the torch part. A main fuel-main oxidant supply part includes: a main fuel supply passage formed in an annular shape on an outer periphery of the torch part; and a main oxidant supply passage formed in an annular shape on an outer periphery of the main fuel supply passage.

Abstract: In a method for operating a combustor of an embodiment, before ignition in the combustor, a mixed gas containing oxygen is circulated through the combustor as a circulating gas. Then, in an operating time from the time of ignition in the combustor to the time of a rated load of a turbine, from the time of ignition until reaching stable combustion conditions allowing stable combustion, a combustion gas in which a controller controls a flow rate of a fuel supplied from a fuel supply part and a flow rate of an oxidant supplied from an oxidant supply part to maintain the same oxygen concentration as an oxygen concentration in the mixed gas is circulated as the circulating gas.

Abstract: A turbine rotor in an embodiment is configured by joining a rotor component member and a rotor component member together by bolt fastening with an abutting end surface of the rotor component member and an abutting end surface of the rotor component member abutting on each other. The turbine rotor includes: a cylindrical recessed portion that is formed at the abutting end surface and is recessed in an axial direction; an axial passage bored from a bottom surface of the cylindrical recessed portion in the axial direction; an introduction passage introducing the cooling medium into the axial passage; a discharge passage discharging the cooling medium from the axial passage; and a sealing member that is arranged in the cylindrical recessed portion and seals one end of the axial passage.

Abstract: A combustor of an embodiment includes: a combustor casing; a combustor liner which is provided in the combustor casing and combusts a fuel and an oxidant to produce a combustion gas; a pipe-shaped member provided to penetrate the combustor casing and the combustor liner; a heat-resistant glass which is provided on the combustor casing side in the pipe-shaped member and closes the pipe-shaped member; a laser light supply mechanism which irradiates an interior of the combustor liner through the heat-resistant glass and an interior of the pipe-shaped member with a laser light; and a contact prevention mechanism which prevents a combustion gas in the combustor liner from coming into contact with the heat-resistant glass.

Abstract: A cushioning member includes: an accommodating bag portion that accommodates a medium; a first fusing portion that defines the accommodating bag portion such that the accommodating bag portion is provided with an opening; a check valve having a first end located inside the accommodating bag portion and a second end located outside the accommodating bag portion, and provided at the opening; a second fusing portion that is immediately adjacent to the first fusing portion on those external sides of the check valve which are opposite in a direction intersecting a direction in which the check valve protrudes from the accommodating bag portion, and defines a channel that communicates with the opening; and a third fusing portion that is connected to the second fusing portion and seals the channel, the third fusing portion being provided across a portion of the check valve that protrudes from the accommodating bag portion.

Abstract: A combustor of an embodiment includes: a combustor casing; a combustor liner which is provided in the combustor casing and combusts a fuel and an oxidant to produce a combustion gas; a pipe-shaped member provided to penetrate the combustor casing and the combustor liner; a heat-resistant glass which is provided on the combustor casing side in the pipe-shaped member and closes the pipe-shaped member; a laser light supply mechanism which irradiates an interior of the combustor liner through the heat-resistant glass and an interior of the pipe-shaped member with a laser light; and a contact prevention mechanism which prevents a combustion gas in the combustor liner from coming into contact with the heat-resistant glass.

Abstract: A turbine rotor in an embodiment includes: a rotor body portion; and a plurality of turbine disks provided on the rotor body portion in a center axis direction of the rotor body portion. The turbine rotor includes: a high-pressure cooling passage formed in the rotor body portion, the high-pressure cooling passage to which a high-pressure cooling medium is supplied, and the high-pressure cooling passage that discharges the high-pressure cooling medium to the high-pressure side turbine stage; and a low-pressure cooling passage formed in the rotor body portion, the low-pressure cooling passage to which a low-pressure cooling medium whose pressure is lower than the pressure of the high-pressure cooling medium is supplied, and the low-pressure cooling passage that discharges the low-pressure cooling medium to the low-pressure side turbine stage.

Abstract: In a method for operating a combustor of an embodiment, before ignition in the combustor, a mixed gas containing oxygen is circulated through the combustor as a circulating gas. Then, in an operating time from the time of ignition in the combustor to the time of a rated load of a turbine, from the time of ignition until reaching stable combustion conditions allowing stable combustion, a combustion gas in which a controller controls a flow rate of a fuel supplied from a fuel supply part and a flow rate of an oxidant supplied from an oxidant supply part to maintain the same oxygen concentration as an oxygen concentration in the mixed gas is circulated as the circulating gas.

Abstract: In a burner of an embodiment, a torch part includes: a torch combustor liner that is provided in a torch part casing and burns a fuel and an oxidant; a torch fuel supply part that supplies a fuel; a torch oxidant supply part that supplies an oxidant; an ignition device that ignites a fuel-air mixture; and a combustion gas pipe that is arranged at the center of the torch part and leads a combustion gas in the torch combustor liner to one end side of the torch part. A main fuel-main oxidant supply part includes: a main fuel supply passage formed in an annular shape on an outer periphery of the torch part; and a main oxidant supply passage formed in an annular shape on an outer periphery of the main fuel supply passage.

Abstract: An entire scroll is effectively cooled. A scroll of an embodiment leads combustion gas to a turbine stage as a working medium for driving a turbine rotor in a gas turbine facility, and includes a scroll inner cylinder and a scroll outer cylinder. The working medium flows into the scroll inner cylinder. The scroll outer cylinder is provided to cover the scroll inner cylinder with a scroll cooling flow path therebetween where a cooling medium with a temperature lower than the working medium is supplied. The scroll cooling flow path includes an inner ring side flow path part located inside than the scroll inner cylinder in a radial direction of the turbine rotor and an outer ring side flow path part located outside than the scroll inner cylinder in the radial direction of the turbine rotor. Here, a dividing part dividing the outer ring side flow path part in an axial direction along a rotation axis of the turbine rotor is provided at the scroll inner cylinder.

Abstract: A combustor structure of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor in a suprecritical CO2 gas turbine which uses supercritical CO2 for a working fluid, a casing of the suprecritical CO2 gas turbine. The combustor structure includes a plurality of combustors. Each of the combustors includes: a combustor liner in a cylindrical shape, which combusts fuel and an oxidant; a fuel supply part which is provided at an upstream end of the combustor liner and supplies the fuel into the combustor liner; and an oxidant supply part which is provided at the upstream end of the combustor liner and supplies the oxidant into the combustor liner.

Abstract: A combustor of an embodiment includes: a cylindrical combustor liner; and a fuel nozzle which is provided at one end of the combustor liner and jets a fuel and an oxidant into the combustor liner. The fuel nozzle includes: a plurality of fuel supply passages which each supply the fuel; and a plurality of oxidant supply passages which each supply the oxidant. Flow rates of the fuel supplied to the respective fuel supply passages and flow rates of the oxidant supplied to the respective oxidant supply passages are each individually regulated.

Abstract: A turbine rotor in an embodiment includes: a rotor body portion; and a plurality of turbine disks provided on the rotor body portion in a center axis direction of the rotor body portion. The turbine rotor includes: a high-pressure cooling passage formed in the rotor body portion, the high-pressure cooling passage to which a high-pressure cooling medium is supplied, and the high-pressure cooling passage that discharges the high-pressure cooling medium to the high-pressure side turbine stage; and a low-pressure cooling passage formed in the rotor body portion, the low-pressure cooling passage to which a low-pressure cooling medium whose pressure is lower than the pressure of the high-pressure cooling medium is supplied, and the low-pressure cooling passage that discharges the low-pressure cooling medium to the low-pressure side turbine stage.

Abstract: A turbine rotor in an embodiment is configured by joining a rotor component member and a rotor component member together by bolt fastening with an abutting end surface of the rotor component member and an abutting end surface of the rotor component member abutting on each other. The turbine rotor includes: a cylindrical recessed portion that is formed at the abutting end surface and is recessed in an axial direction; an axial passage bored from a bottom surface of the cylindrical recessed portion in the axial direction; an introduction passage introducing the cooling medium into the axial passage; a discharge passage discharging the cooling medium from the axial passage; and a sealing member that is arranged in the cylindrical recessed portion and seals one end of the axial passage.

Abstract: A double pipe of an embodiment includes: an outer pipe; an inner pipe inserted through an interior of the outer pipe to make high-temperature carbon dioxide flow therethrough; and an opening of the outer pipe which introduces low-temperature carbon dioxide to an annular passage between the outer pipe and the inner pipe. The double pipe further includes: an inner pipe protruding part protruding from an outer peripheral surface of the inner pipe to a radial outside; and an outer pipe protruding part protruding from an inner peripheral surface of the outer pipe to a radial inside, the outer pipe protruding part having a fitting groove fitted to the inner pipe protruding part and penetrating in an axial direction.

Abstract: A transition piece of an embodiment leads a combustion gas generated by a combustor liner to a turbine part in a gas turbine facility. An outlet portion from which the combustion gas flows out to the turbine part in the transition piece includes: an inner peripheral wall located inside in a radial direction of the turbine part; an outer peripheral wall located further outside than the inner peripheral wall in the radial direction; and support struts provided between the inner peripheral wall and the outer peripheral wall. In the inner peripheral wall, first insertion grooves are formed. In the outer peripheral wall, second insertion grooves are formed. In the support struts, first end portions located inside in the radial direction are inserted into and fixed in the first insertion grooves, and second end portions located outside in the radial direction are inserted into and fixed in the second insertion grooves.

Abstract: A combustor of an embodiment includes: a combustor casing; a combustor liner which is provided in the combustor casing and combusts a fuel and an oxidant to produce a combustion gas; a pipe-shaped member provided to penetrate the combustor casing and the combustor liner; a heat-resistant glass which is provided on the combustor casing side in the pipe-shaped member and closes the pipe-shaped member; a laser light supply mechanism which irradiates an interior of the combustor liner through the heat-resistant glass and an interior of the pipe-shaped member with a laser light; and a contact prevention mechanism which prevents a combustion gas in the combustor liner from coming into contact with the heat-resistant glass.

Abstract: A combustor according to an embodiment includes: a cylinder body that demarcates a space between a combustor casing and a combustor liner; a pipe that guides a combustion gas between the combustor liner and the cylinder body; a pipe that guides a combustion gas having a temperature lower than a combustion gas to be guided to the pipe between the combustor casing and the cylinder body; a pipe-shaped member provided so as to penetrate the combustor casing, the cylinder body, and the combustor liner; a heat-resistant glass that is provided in the pipe-shaped member; a condensing lens provided in a manner to face the heat-resistant glass; and a laser oscillator that emits laser light to the inside of the combustor liner through the condensing lens.

Abstract: The embodiment prevents the buckling of a combustor liner without causing any increase in thermal stress when applied to a plant that uses supercritical carbon dioxide as a working fluid. A gas turbine combustor includes: a fuel nozzle; a cylindrical combustor liner provided downstream of the fuel nozzle; and a transition piece provided downstream of the combustor liner to guide a fuel gas to a gas turbine stator blade, wherein the combustor liner is divided into and composed of a plurality of liner composing members which are coupled in an axial direction.

Abstract: An entire scroll is effectively cooled. A scroll of an embodiment leads combustion gas to a turbine stage as a working medium for driving a turbine rotor in a gas turbine facility, and includes a scroll inner cylinder and a scroll outer cylinder. The working medium flows into the scroll inner cylinder. The scroll outer cylinder is provided to cover the scroll inner cylinder with a scroll cooling flow path therebetween where a cooling medium with a temperature lower than the working medium is supplied. The scroll cooling flow path includes an inner ring side flow path part located inside than the scroll inner cylinder in a radial direction of the turbine rotor and an outer ring side flow path part located outside than the scroll inner cylinder in the radial direction of the turbine rotor. Here, a dividing part dividing the outer ring side flow path part in an axial direction along a rotation axis of the turbine rotor is provided at the scroll inner cylinder.