Kawasaki Jukogyo Kabushiki Kaisha

Japan Aerospace Exploration Agency

Tokyo Metropolitan Public University Corporation

Takeo Oda

Masayoshi Kobayashi

Hiroyuki Ninomiya

Atsushi Horikawa

Yasuhiro Kinoshita

Hitoshi Fujiwara

Ryusuke Matsuyama

Hideki Ogata

Masahiro Ogata

Hideshi Yamada

Shigeru Hayashi

Masahide Kazari

Seiji Yamashita

Tomoko Tsuru

Kunio Okada

Kazuo Shimodaira

Takeo Nishiura

Osamu Hisamatsu

Hiroaki Miyamoto

Takeshi Takagi

Takaya Hamamoto

Takahiro Uto

Kazuaki Matsuura

Hirotaka Kurashima

Kohshi Hirano

Youji Kurosawa

Takashi Sakurai

Hiroyuki Kashihara

Kiyoshi Matsumoto

Koichi Nozaki

Toshiaki Sakurazawa

Ryosuke Oshima

Saburo Yuasa

Atushi Horikawa

A combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.

Combustor liner

A burner device for supplying a mixture of a fuel gas and a combustion-supporting gas into a combustion region includes: a mixing path configured to inject the mixture from a downstream end portion of the mixing path into the combustion region; a fuel gas injection nozzle configured to inject the fuel gas into the mixing path toward the combustion region; and a combustion-supporting gas supply swirler configured to inject the combustion-supporting gas such that at least a part of the combustion-supporting gas collides directly with the fuel gas injected from the fuel gas injection nozzle, in a direction of a tangent line that is tangent to a fuel injection hole of the fuel gas injection nozzle on a cross-section.

Burner device

A main fuel injector of a fuel injection device includes: a main outer air passage including an inlet that is open outward in a radial direction, the main outer air passage taking in compressed air through the inlet; a main inner air passage including an inlet that is open inward in the radial direction, the main inner air passage taking in the compressed air through the inlet; a merged air passage, in which the compressed air taken in by the main outer air passage and the compressed air taken in by the main inner air passage merge together; and a main fuel injection port configured to inject a fuel into the compressed air taken in by the main outer air passage or into the compressed air taken in by the main inner air passage.

Fuel injection device

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 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 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.

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

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.

Gas turbine combustor

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

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

Multifuel gas turbine combustor

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.

Pilot fuel injector with swirler

This invention provides a gas turbine combustor including: a main burner at a head portion of a combustor cylinder; and a pre-mixing type supplemental burner at a downstream portion of the combustor cylinder and extending through a circumferential wall thereof. The supplemental burner includes: an introducing passage configured to deflect a part of the compressed air radially inward, the compressed air flowing from an air passage between the circumferential wall of the combustor cylinder and a housing surrounding the circumferential wall toward the head portion of the combustor cylinder, and introduce the compressed air into the combustor cylinder; and a fuel nozzle configured to supply the fuel from fuel injection holes to the compressed air introduced into the introducing passage to produce a pre-mixed gas in the introducing passage.

Gas turbine combustor including separate fuel injectors for plural zones

The present combustor of gas turbine engine includes: a fuel injection unit including a fuel spray part to spray a fuel so that a diffusion combustion region is formed in a combustion chamber, and a pre-mixture supply part to supply a pre-mixture of a fuel and an air so that a pre-mixture combustion region is formed in the combustion chamber; and a fuel supply unit to supply the fuel to the fuel spray part and pre-mixture supply part. The fuel supply unit includes: a pilot fuel passage and a main fuel passage to supply the fuel to the fuel spray part and the pre-mixture supply part, respectively; an assembled fuel passage to supply the fuel to the pilot and main fuel passages; and a fuel distributor disposed at a branch point where the assembled fuel passage is connected to both the pilot and main fuel passages. The fuel distributor is configured to automatically control amounts of the fuel to be distributed to the pilot fuel passage and to the main fuel passage in accordance with the fuel pressure.

Growing community of inventors

Kobe, Japan

Takeo Oda