Kawasaki Jukogyo Kabushiki Kaisha

B&b Agema Gmbh

Kunio Okada

Atsushi Horikawa

Masahide Kazari

Takeo Oda

Seiji Yamashita

Karsten Kusterer

Junichi Kitajima

Takahiro Uto

Kohshi Hirano

Harald Funke

Anis Haj Ayed

Kazuki Koga

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.

Gas turbine combustor

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.

Growing community of inventors

Kakogawa, Japan

Kunio Okada