Kawasaki Jukogyo Kabushiki Kaisha

B&b Agema Gmbh

Junichi Kitajima

Atsushi Horikawa

Masahide Kazari

Hiroyuki Kashihara

Kazuo Tanaka

Takatoshi Shoji

Seiji Yamashita

Kunio Okada

Karsten Kusterer

Takeshi Kimura

Eiichi Harada

Kenji Mori

Kiyoshi Matsumoto

Shinichi Kajita

Yasushi Yoshino

Anis Haj Ayed

Harald Funke

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

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

A combustor, in which a flame holding region is formed at a location distant from a pilot burner to avoid burnout of the pilot burner and in which flame holding capability is increased to use a lean pre-mix gas for reducing NOx emission, is provided. The combustor includes a combustion liner having a cylindrical side wall that defines a combustion chamber; and a main burner positioned at a top portion of the combustion liner for injecting an annular pre-mix gas into the combustion chamber to form a reverse flow region at a downstream portion thereof, which region is oriented towards the top portion of the combustion chamber along a longitudinal axis. In this combustor, a pilot burner is arranged at the top portion for injecting a mixture of fuel and air only in a direction confronting the reverse flow region.

Combustor

A fuel cell-atmospheric-pressure turbine hybrid system uses the thermal energy of a cell exhaust gas discharged from an atmospheric-pressure, high-temperature fuel cell effectively, does not need any additional emergency protective device, and enables the use of lightweight, easy-to-process structural and piping materials to reduces the cost. The fuel cell-atmospheric-pressure turbine hybrid system includes: a combustorfor burning an exhaust gas Gdischarged from an atmospheric-pressure, high-temperature fuel cell; a turbinein which a combustion gas Gdischarged from the combustorexpands and the pressure of the combustion gas Gdrops to a negative pressure; a compressorfor compressing an exhaust gas Gdischarged from the turbineto increase the pressure of the exhaust gas G; and a heat exchangerfor transferring heat from the high-temperature exhaust gas Gdischarged from the turbineto low-temperature air A to be supplied to the fuel cell

Fuel cell-atmospheric-pressure turbine hybrid system

A combustor device of a gas turbine engine, which combustor device is supplied with compressed air from a compressor and delivers combustion gas to a turbine, comprises an outer casing and an inner casing defining therein a combustion chamber and forming between the outer and inner casings an annular passage for the intake of the compressed air, a swirler opening being provided at the innermost end of the inner casing for taking the compressed air into the combustion chamber. Swirling motion of the compressed air around the inlet of the swirler opening, which causes static pressure drop at the swirler opening inlet and resultant undesirable combustion, is effectively prevented by providing swirl preventing vanes between the inner and outer casings. When the swirl preventing vanes are provided near the swirler opening, guide vanes may be provided near the upstream end of the annular passage to intentionally impart swirling motion to the compressed air to prevent non-uniform distribution of the supplied compressed air.

Combustor device of gas turbine engine

Growing community of inventors

Akashi, Japan

Junichi Kitajima