Kawasaki Jukogyo Kabushiki Kaisha

Japan Aerospace Exploration Agency

B&b Agema Gmbh

Atsushi Horikawa

Kunio Okada

Takeo Oda

Ryusuke Matsuyama

Hitoshi Fujiwara

Masayoshi Kobayashi

Masahide Kazari

Junichi Kitajima

Hideshi Yamada

Shigeru Hayashi

Hideki Ogata

Seiji Yamashita

Kazuo Shimodaira

Hiroyuki Kashihara

Kazuaki Matsuura

Youji Kurosawa

Karsten Kusterer

Yoshichika Sato

Takeshi Kimura

Kenta Yamaguchi

Takahiro Uto

Kiyoshi Matsumoto

Kohshi Hirano

Yasushi Yoshino

Daniel Kroniger

Hiromu Kamiya

Harald Funke

Yuta Uchiyama

Kazuki Koga

Anis Haj Ayed

A gas turbine combustor includes: a tubular body; an air passage; and a resonator. The air passage includes: an upstream region that extends along an outer peripheral surface of the tubular body; a downstream region that extends along an inner peripheral surface of the tubular body and is located at a first side of the combustion chamber in the axial direction; and a direction change region that connects the upstream region to the downstream region in a radial direction of the tubular body and is adjacent to the upstream region such that an area of a section of the air passage which is orthogonal to the axial direction changes at a position between the upstream region and the direction change region. The opening is open toward a space of the air passage which is located downstream of the upstream region.

Gas turbine combustor

A gas turbine combustor includes a fuel injection device provided to a combustion tube forming a combustion chamber on an inner side, and including: a fuel injection portion having a plurality of fuel injection holes which inject fuel in directions containing components perpendicular to an axial direction and a common fuel supply chamber which supplies fuel into the plurality of fuel injection holes; and an air guide portion which guides air to fuel injected from each fuel injection hole. The fuel injection portion has an air guide surface which guides air for combustion and is located frontward in the axial direction of the combustion chamber relative to the fuel injection hole. A fuel injection opening of the fuel injection hole is provided at a bottom wall surface of a stepped recess recessed in a step shape from the air guide surface.

A premixed combustion burner includes: a mixing part including a first peripheral wall having a center burner axis, a mixing region for mixing fuel and air in the first peripheral wall, and air supply ports arranged circumferentially and open in the first peripheral wall; a nozzle on the mixing part side, a second peripheral wall having a center burner axis, a premixed gas passage continuous to the second peripheral wall mixing region, and a cooling passage in the second peripheral wall; and a header part proximal to the mixing part, and a first header chamber with a fuel supply port, second header chamber, and fuel ejection port for communication between the second header chamber and mixing region. The first peripheral wall has an outward path connecting the first header chamber and a cooling passage inlet, and a return path connecting cooling passage outlet and the second header chamber.

Premixed combustion burner

A gas turbine combustor including a fuel injector having a plurality of annular fuel injection portions in each of which multiple fuel injection holes are formed, is provided with: an auxiliary fuel introduction passage for introducing an auxiliary fuel that is to be supplied to an auxiliary fuel injection portion that is a part of the plurality of annular fuel injection portions, into the fuel injector; a first main fuel introduction passage provided with a flow regulating valve for introducing a main fuel that is to be supplied to a main fuel injection portion that is an annular fuel injection portion other than the auxiliary fuel injection portion, into the fuel injector; and a second main fuel introduction passage provided with a flow regulating valve for introducing the main fuel that is to be supplied to the auxiliary fuel injection portion, into the fuel injector.

Gas turbine combustor and operating method thereof

Provided is a combustor used in a gas turbine and configured to mix and burn fuel gas, water vapor, and air. The combustor includes: a fuel injection device including a fuel injection portion which directly injects the fuel gas into a combustion chamber, and a water vapor injection portion provided in at least one of a position radially outward of the fuel injection portion and a position radially inward of the fuel injection portion; and an air supply chamber which is provided in at least one of a position radially outward of the water vapor injection portion provided radially outward of the fuel injection portion and a position radially inward of the water vapor injection portion provided radially inward of the fuel injection portion, and which supplies air to be mixed with water vapor injected from the water vapor injection portion.

A combustor includes: a combustion liner having a combustion chamber formed therein; and a fuel injector mounted to a top portion of the combustion liner, and including a fuel injection member having a plurality of fuel injection annular portions and an air guide member including a plurality of combustion air annular portions that guide air for combustion. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately. The fuel injector injects fuel and air into the combustion chamber. Each of the fuel injection annular portions includes a plurality of fuel injection holes that are open in a radial direction thereof, and each of the combustion air annular portions includes a plurality of air guide grooves that are open in an axial direction thereof, and guide the air to the fuel jetted from the fuel injection holes.

Combustor for gas turbine engine

A fuel injection nozzle () of the present invention comprises a pre-mixing passage () which mixes fuel () and air () to generate an air-fuel mixture; and an injection port () which is located downstream of the pre-mixing passage () and injects the air-fuel mixture into a combustion chamber (). The fuel injection port () has a slit shape and a width that is less than a dimension that is twice as large as a quenching distance.

Fuel injection nozzle, fuel injection module and gas turbine

A fuel injection device, for a gas turbine, which enhances uniform distribution in concentration of fuel gas and water vapor in a combustion chamber with a simple structure and at low cost to effectively reduce NOx, is provided. The fuel injection device mixes fuel gas and water vapor and injects fuel gas and water vapor into a combustion chamber. The fuel injection device includes a nozzle housing having a mixing chamber, and the nozzle housing includes a first introduction passage to introduce fuel gas from an outer circumference of the nozzle housing in a circumferential direction of the mixing chamber; and a second introduction passage to introduce water vapor from the outer circumference of the nozzle housing in a circumferential direction of the mixing chamber. Fuel gas and water vapor are swirled about an axis C of the mixing chamber and mixed in the mixing chamber.

Fuel injection device for gas turbine

A fuel injection device, for a gas turbine, which enhances uniform distribution in concentration of fuel gas and water vapor in a combustion chamber with simple structure and at low cost to effectively reduce NOx, is provided. The fuel injection device with a fuel nozzle to mix fuel gas and water vapor and inject the fuel gas and water vapor into a combustion chamber, includes: a nozzle housing having a mixing chamber thereinside; a first introduction passage to introduce the fuel gas into the mixing chamber from outside of the nozzle housing; and a second introduction passage to introduce the water vapor into the mixing chamber from an outside of the nozzle housing; and a plurality of reverse passages communicating with a downstream end of the mixing chamber and configured to allow for a plurality of reverses of flow of mixed gas from the mixing chamber.

A fuel injector () comprises a cylindrical passage () which opens in a combustion chamber (), a fuel introduction passage () which guides fuel to a region of the cylindrical passage () which is closer to the combustion chamber (), and an air introduction passage () which guides compressed air to the cylindrical passage () at a location that is upstream of a location at which the fuel is introduced to the cylindrical passage (), wherein the fuel introduction passage () guides the fuel in a tangential direction of the cylindrical passage () in a transverse sectional view.

Fuel injector and gas turbine

A fuel injection device for supplying a fuel to a compressed air includes: a pilot fuel injector; a main fuel injector located at an outer periphery of the pilot fuel injector; and an air injection unit located between an outlet end portion of the pilot fuel injector and the main fuel injector. The air injection unit includes: a partition wall plate separating the air injection unit from a combustion chamber; a flame stabilization plate provided at a downstream side of the partition wall plate; a first opening at a downstream side between the flame stabilization plate and the outlet end portion of the pilot fuel injector; and a second opening provided in the partition wall plate and through which the compressed air is supplied. The flame stabilization plate includes an inclined portion inclined in a radially outward and downstream direction with respect to an axis.

Fuel injection device

The gas turbine system (GT) includes a combustor () having a fuel injection nozzle assembly () for jetting hydrogen gas (H) and pure water (W), a reservoir () for pooling the pure water (W) to be supplied to the combustor (), a gas compressing device () for boosting the hydrogen gas (H) to be supplied to the combustor (), a fuel supply passage () for guiding the boosted hydrogen gas (H) towards the combustor (), and a pressurizing passage () communicating between the reservoir () and the fuel supply passage () for pressurizing the pure water (W) by means of the boosted hydrogen gas (H).

Gas turbine system with injection water pressurization passage

An annular type gas turbine combustor having a plurality of fuel nozzle assemblies () on a circumference includes a pilot nozzle unit () for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle () into a combustion chamber (), a main nozzle unit () provided so as to surround the pilot nozzle unit () for spraying a fuel for premix combustion, and a flow guide () disposed on a downstream side of each of the fuel nozzle assemblies () and having a sectional area of a passage for air and air-fuel mixture from each of the fuel nozzle assemblies (), which gradually increase in a downstream direction.

A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the main injector includes: a first inflow channel through which the air having a major flow component in an axial direction is taken; a second inflow channel through which the air having a major flow component in a radial direction is taken and which causes the air therein to meet the air from the first inflow channel; and a main fuel injecting portion configured to inject the fuel only to the second inflow channel.

Fuel injector with radial and axial air inflow

A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the pilot injector includes: a center nozzle configured to eject air jet flowing straight in an axial direction on a central axis of the pilot injector; an inside swirler provided on a radially outer side of the center nozzle and configured to cause inflow air to swirl around the central axis; and a pilot fuel injecting portion configured to inject the fuel from between the center nozzle and the inside swirler to air flow in the center nozzle.

Growing community of inventors

Akashi, Japan

Atsushi Horikawa