Toshiba Energy Systems & Solutions Corporation

Kabushiki Kaisha Toshiba

Yuichi Morisawa

Masao Itoh

Yasunori Iwai

Hiroki Kasuya

Shinju Suzuki

Yasuaki Nakamura

Yoshihisa Kobayashi

Takashi Sasaki

Hideyuki Maeda

Jeremy Eron Fetvedt

Iwataro Sato

Hideaki Shimada

Tomomi Okuyama

Takahiro Nakanishi

Ryu Hirayama

Kojiro Tada

Rodney John Allam

A combined cycle power generation facility of an embodiment includes a first heat recovery steam generator including a high-pressure steam generation part using an exhaust gas of a gas turbine and a reheat part; a high-pressure turbine to which steam is introduced from the high-pressure steam generation part; a combustor which combusts hydrogen and oxygen; a reheat steam pipe connecting the high-pressure turbine and the combustor with the reheat part interposed therebetween; an oxygen-hydrogen combustion turbine to which steam is introduced from the combustor; a second heat recovery steam generator including a steam generation part using an exhaust gas of the oxygen-hydrogen combustion turbine; a low-pressure turbine to which steam is introduced from the steam generation part; and a condenser which steam is introduced from the low-pressure turbine.

Combined cycle power generation facility

A combustor structure of an embodiment includes: a plurality of combustors; a rear liner which guides a combustion gas from the plurality of combustors to a downstream side; and a scroll which guides the combustion gas from the rear liner in an axial direction and a circumferential direction of a turbine rotor. Each of the combustors includes: a combustor liner; a fuel supply part which supplies fuel into the combustor liner; and an oxidant supply part which supplies a swirling flow of an oxidant from the circumference of the fuel supply part into the combustor liner. The plurality of combustors include: the combustor in which a swirling direction of the swirling flow of the oxidant is clockwise; and the combustor in which a swirling direction of the swirling flow of the oxidant is counterclockwise.

Gas turbine combustor structure

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.

Gas turbine combustor

A combustor structure of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor in a supercritical COgas turbine which uses supercritical COfor a working fluid, a casing of the supercritical COgas 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.

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.

Burner with torch ignition mechanism and operation method thereof

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.

Method for operating gas turbine combustor

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.

Scroll and gas turbine facility

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.

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.

Transition piece

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.

Gas turbine combustor including laser ignition

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.

Gas turbine facility exhaust gas supply heat exchange arrangement

An ignition device of an embodiment is provided to a gas turbine combustor to which supercritical-pressure COis 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.

Ignition device and gas turbine combustor

A gas turbine facilityof an embodiment includes: a combustor; a cylinderdividing a space between a combustor casingand the combustor; and a turbinerotated by a combustion gas exhausted from the combustor. The gas turbine facilityincludes: a heat exchangerwhich cools the combustion gas; a pipethrough which a part of the combustion gas cooled in the heat exchangerpasses in the heat exchangerto be heated and is guided to a space between the combustorand the cylinder; a pipewhich guides another part of the combustion gas cooled in the heat exchangerto a space between the combustor casingand the cylinder; and a pipewhich exhausts a remaining part of the combustion gas cooled in the heat exchangerto the outside.

Gas turbine facility

A gas turbine facilityin an embodiment includes: a combustor; a fuel nozzle; a turbine; a heat exchangercooling the combustion gas. The gas turbine facilityincludes: a pipeguiding a part of the cooled combustion gas to an oxidant supply pipe; a pipepassing a mixed gas composed of the oxidant and the combustion gas through the heat exchangerto heat it, and guising it to the fuel nozzle; a pipepassing another part of the cooled combustion gas through the heat exchangerto heat it, and guiding it to the combustor; a pipepassing still another part of the cooled combustion gas through the heat exchangerto heat it, and guiding it to the fuel nozzle; and a pipeexhausting a remaining part of the cooled combustion gas.

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Yokohama, Japan

Yuichi Morisawa