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.

Abstract: The gas turbine facility 10 of the embodiment includes a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas, a heat exchanger 23 cooling the combustion gas, a heat exchanger 24 removing water vapor from the combustion gas which passed through the heat exchanger 23 to regenerate dry working gas, and a compressor 25 compressing the dry working gas until it becomes supercritical fluid. Further, the gas turbine facility 10 includes a pipe 42 guiding a part of the dry working gas from the compressor 25 to the combustor 20 via the heat exchanger 23, a pipe 44 exhausting a part of the dry working gas to the outside, and a pipe 45 introducing a remaining part of the dry working gas exhausted from the compressor 25 into a pipe 40 coupling an outlet of the turbine 21 and an inlet of the heat exchanger 23.

Abstract: A gas turbine facility 10 of an embodiment has a combustor 20 combusting fuel and oxidant, a turbine 28 rotated by combustion gas exhausted from the combustor 20, a heat exchanger 25 cooling the combustion gas from the turbine 28, a pipe 46 guiding a part of the combustion gas to the combustor 20 via the heat exchanger 25, and a pipe 45 exhausting a remaining part of the combustion gas to an outside. Further, the facility has a pipe 40 supplying fuel to the combustor 20, a pipe 41 supplying oxidant to the combustor 20 via the heat exchanger 25, and a pipe 42 branched from the pipe 41, bypassing the heat exchanger 25, and coupled to the pipe 41, so as to introduce the oxidant into the pipe 41.

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 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 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: It has been found that a compound of the general formula (I) having an isoxazole skeleton has excellent inhibitory activity against mutant IDH1 protein and inhibits the production of 2-HG by this protein, while the compound is also capable of effectively inhibiting the growth of various tumors expressing the protein. In the formula, R1, R2, R3, Y, and Z are as defined in claim 1.

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: It has been found that a compound of the general formula (I) having an isoxazole skeleton has excellent inhibitory activity against mutant IDH1 protein and inhibits the production of 2-HG by this protein, while the compound is also capable of effectively inhibiting the growth of various tumors expressing the protein. In the formula, R1, R2, R3, Y, and Z are as defined in claim 1.

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: The gas turbine facility 10 of the embodiment includes a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas, a heat exchanger 23 cooling the combustion gas, a heat exchanger 24 removing water vapor from the combustion gas which passed through the heat exchanger 23 to regenerate dry working gas, and a compressor 25 compressing the dry working gas until it becomes supercritical fluid. Further, the gas turbine facility 10 includes a pipe 42 guiding a part of the dry working gas from the compressor 25 to the combustor 20 via the heat exchanger 23, a pipe 44 exhausting a part of the dry working gas to the outside, and a pipe 45 introducing a remaining part of the dry working gas exhausted from the compressor 25 into a pipe 40 coupling an outlet of the turbine 21 and an inlet of the heat exchanger 23.