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 gas turbine facility 10 of an embodiment has a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas exhausted from the combustor 20, and a pipe 41 guiding a part of the combustion gas exhausted from the turbine 21 to a pipe 42 supplying the oxidant. Further, the gas turbine facility 10 has a pipe 43 guiding mixed gas constituted of the oxidant and the combustion gas to the combustor 20, a pipe 45 guiding another part of the combustion gas to the combustor 20 as working fluid of the turbine, and a pipe 40 exhausting a remaining part of the combustion gas to an outside.

Abstract: A gas turbine facility of an embodiment includes: a combustor casing; a combustor provided in the combustor casing; a cylinder surrounding a periphery of the combustor and dividing a space between the combustor casing and the combustor; a turbine rotated by combustion gas exhausted from the combustor; a heat exchanger cooling the combustion gas exhausted from the turbine; a pipe through which a part of the combustion gas cooled in the heat exchanger passes in the heat exchanger to be heated, the pipe guiding the combustion gas heated in the heat exchanger into the cylinder; and a pipe guiding another part of the combustion gas cooled in the heat exchanger to a space between the combustor casing and the cylinder.

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: An ignition device of an embodiment is provided to a gas turbine combustor to which supercritical-pressure CO2 is introduced. The ignition device includes: a shutoff valve provided on an outer side face of a casing of the combustor to make the inside of the casing and the outside of the casing communicate with each other or shut off from each other; an ignition rod formed of a long rod including a spark discharge portion at a leading end, and capable of advancing to and retreating from the inside of a combustor liner provided in the casing from/to the outside of the casing through the shutoff valve; and a driving part which makes the ignition rod advance and retreat.

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 gas turbine facility 10 of an embodiment includes: a combustor 20; a cylinder 80 dividing a space between a combustor casing 70 and the combustor 20; and a turbine 25 rotated by a combustion gas exhausted from the combustor 20. The gas turbine facility 10 includes: a heat exchanger 24 which cools the combustion gas; a pipe 42 through which a part of the combustion gas cooled in the heat exchanger 24 passes in the heat exchanger 24 to be heated and is guided to a space between the combustor 20 and the cylinder 80; a pipe 44 which guides another part of the combustion gas cooled in the heat exchanger 24 to a space between the combustor casing 70 and the cylinder 80; and a pipe 45 which exhausts a remaining part of the combustion gas cooled in the heat exchanger 24 to the outside.

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: A gas turbine facility 10 in an embodiment includes: a combustor 20; a fuel nozzle 21; a turbine 22; a heat exchanger 24 cooling the combustion gas. The gas turbine facility 10 includes: a pipe 42 guiding a part of the cooled combustion gas to an oxidant supply pipe; a pipe 44 passing a mixed gas composed of the oxidant and the combustion gas through the heat exchanger 24 to heat it, and guising it to the fuel nozzle 21; a pipe 40 passing another part of the cooled combustion gas through the heat exchanger 24 to heat it, and guiding it to the combustor 20; a pipe 45 passing still another part of the cooled combustion gas through the heat exchanger 24 to heat it, and guiding it to the fuel nozzle 21; and a pipe 46 exhausting a remaining part of the cooled combustion gas.

Abstract: An ignition device of an embodiment is provided to a gas turbine combustor to which supercritical-pressure CO2 is introduced. The ignition device includes: a shutoff valve provided on an outer side face of a casing of the combustor to make the inside of the casing and the outside of the casing communicate with each other or shut off from each other; an ignition rod formed of a long rod including a spark discharge portion at a leading end, and capable of advancing to and retreating from the inside of a combustor liner provided in the casing from/to the outside of the casing through the shutoff valve; and a driving part which makes the ignition rod advance and retreat.

Abstract: A gas turbine facility of an embodiment includes: a combustor casing; a combustor provided in the combustor casing; a cylinder surrounding a periphery of the combustor and dividing a space between the combustor casing and the combustor; a turbine rotated by combustion gas exhausted from the combustor; a heat exchanger cooling the combustion gas exhausted from the turbine; a pipe through which a part of the combustion gas cooled in the heat exchanger passes in the heat exchanger to be heated, the pipe guiding the combustion gas heated in the heat exchanger into the cylinder; and a pipe guiding another part of the combustion gas cooled in the heat exchanger to a space between the combustor casing and the cylinder.

Abstract: A gas turbine facility 10 of an embodiment includes: a combustor 20; a cylinder 80 dividing a space between a combustor casing 70 and the combustor 20; and a turbine 25 rotated by a combustion gas exhausted from the combustor 20. The gas turbine facility 10 includes: a heat exchanger 24 which cools the combustion gas; a pipe 42 through which a part of the combustion gas cooled in the heat exchanger 24 passes in the heat exchanger 24 to be heated and is guided to a space between the combustor 20 and the cylinder 80; a pipe 44 which guides another part of the combustion gas cooled in the heat exchanger 24 to a space between the combustor casing 70 and the cylinder 80; and a pipe 45 which exhausts a remaining part of the combustion gas cooled in the heat exchanger 24 to the outside.

Abstract: A gas turbine facility 10 in an embodiment includes: a combustor 20; a fuel nozzle 21; a turbine 22; a heat exchanger 24 cooling the combustion gas. The gas turbine facility 10 includes: a pipe 42 guiding a part of the cooled combustion gas to an oxidant supply pipe; a pipe 44 passing a mixed gas composed of the oxidant and the combustion gas through the heat exchanger 24 to heat it, and guising it to the fuel nozzle 21; a pipe 40 passing another part of the cooled combustion gas through the heat exchanger 24 to heat it, and guiding it to the combustor 20; a pipe 45 passing still another part of the cooled combustion gas through the heat exchanger 24 to heat it, and guiding it to the fuel nozzle 21; and a pipe 46 exhausting a remaining part of the cooled combustion gas.

Abstract: A gas turbine facility 10 of an embodiment has a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas exhausted from the combustor 20, and a pipe 41 guiding a part of the combustion gas exhausted from the turbine 21 to a pipe 42 supplying the oxidant. Further, the gas turbine facility 10 has a pipe 43 guiding mixed gas constituted of the oxidant and the combustion gas to the combustor 20, a pipe 45 guiding another part of the combustion gas to the combustor 20 as working fluid of the turbine, and a pipe 40 exhausting a remaining part of the combustion gas to an outside.