Kawasaki Jukogyo Kabushiki Kaisha

Masahiro Ogata

Takeo Oda

Yasuhiro Kinoshita

Takahiro Uto

Kohshi Hirano

Makoto Gouda

Yasufumi Hosokawa

Muneyuki Nishi

Mitsugu Ashikaga

Tsuyoshi Sato

So Kurosaka

The present invention provides a burner, a combustor equipped with the burner, and a gas turbine, with which it is possible to premix a first hydrocarbon-based fuel (for example, natural gas), a second fuel (for example, hydrogen gas), and combustion air, and to spray into the combustion chamber of the combustor a thin and uniform concentration distribution of the premixed air, and with which it is possible to suppress the amount of NOx discharged. On the upstream side of the premix flow path, hydrogen gas is sprayed from second fuel spray nozzles, which project into the premix flow path, into the flow of the combustion air flowing toward the center from the outer edge of an outer cylinder, whereby a primary air-fuel mixture having a uniform concentration distribution is generated without affecting a low-speed region of the combustion air. Natural gas is then sprayed from first fuel spray nozzles into the primary air-fuel mixture, whereby the natural gas, which has a high specific gravity, and the primary air-fuel mixture are adequately mixed in a stirring fashion, and a secondary air-fuel mixture (premixed air) is generated that is lean and has a more uniform concentration distribution than the first air-fuel mixture. By combusting this type of premixed air in the combustion chamber, NOx in the combustion exhaust gas can be suppressed.

Burner, combustor, and gas turbine

A burner injects a mixture of fuel and air from a base end side far from a combustion chamber toward a distal end side close to the combustion chamber. The burner has a fuel passage having a turn-back part turning back and channeling the fuel between the base end side and the distal end side. The burner has a premixed gas passage formed to surround the fuel passage. The burner has a fuel introduction part introducing the fuel channeled through the fuel passage into the premixed gas passage from the base end side to the distal end side. The burner has an air supply part supplying the premixed gas passage with air on the base end side.

To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner () for supplying to and combusting a premixed gas (M), containing a first fuel (F), within a first combustion region (S) of a combustion chamber (), and a supplemental burner () for supplying to and combusting a second fuel (F) of a composition different from that of the first fuel (F) within a second combustion region (S) defined downstream of the first combustion region (S) within the combustion chamber (). The first fuel (F) is of a hydrocarbon system and the second fuel (F) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.

Multifuel gas turbine combustor with fuel mixing chamber and supplemental burner

Multifuel gas turbine combustor

A gas turbine engine includes: an air flow control system installed in an air intake path for introducing air to a compressor. The air intake path is located outside and upstream with respect to the compressor. The engine also includes intake air flow control means for controlling an intake air flow by operating the air flow control system according to a load of the engine so as to maintain an air-to-fuel ratio in the combustor within a proper range suited to suppress a discharge of an atmospheric pollutant.

Gas turbine engine with intake air flow control mechanism

Growing community of inventors

Kobe, Japan

Masahiro Ogata