Hitachi, Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Koji Kato

Hiroshi Inoue

Nariyoshi Kobayashi

Isao Takehara

Tomomi Koganezawa

Yoshitaka Hirata

Shouhei Yoshida

Tomoya Murota

Tomohiro Asai

Kazuhito Koyama

Toshifumi Sasao

Kazuyuki Itou

Keisuke Miura

Michio Kuroda

Yoji Ishibashi

Kazumi Iwai

Minoru Kanoi

Takeo Saito

Kazuo Nishijima

Takashi Hashimoto

Akinori Hayashi

Kazuyuki Ito

Takashi Ohmori

Fumio Kato

Shigeyuki Akatsu

Yoshio Okamoto

Shohei Yoshida

Mitsuru Nakamura

Katsukuni Hisano

Satoshi Dodo

Junzo Kawakami

Akira Arai

Yoshifumi Kunugi

Nobuo Tsumaki

Hiroyuki Kudo

Kiyoji Iwashita

Satoshi Tsukahara

Masaya Ohtsuka

Terunobu Miyazaki

Toru Takei

Tadashi Shinozaki

Yuzuru Imamura

Saburou Yasukawa

Akira Yamagiwa

Hitoshi Matsushima

Shozo Nakamura

Kanji Otsuka

Toshio Hatada

Hiromitsu Tokisue

Kazuhiko Kawaike

Hiraku Ikeda

Hidetaro Murata

Hiromi Koizumi

Yuji Shirai

Hidekazu Fujimura

Tatsuya Sekiguchi

Seiichi Kirikami

Muneo Mizumoto

Takao Ohba

Yasuhiko Otawara

Noriyuki Hayashi

Tsunemasa Nishijima

Tamio Innami

Yoshihiro Kondou

Takeo Saitou

Shigeyuki Yamazaki

Kazuyuki Itoh

Tsunemasa Nishijama

An object of the invention is to provide a reliable gas turbine combustor that can provide lowered NOx and combustion stability. The gas turbine combustor includes a combustion chamber to which fuel and air are supplied; a first burner located on the upstream side of the combustion chamber, the first burner jetting fuel into the combustion chamber and jetting air into the combustion chamber in a swirling manner; a plurality of second burners arranged around the first burner and supplying a premixed gas of air and fuel to the combustion chamber; an annular bulkhead disposed between the first burner and the second burners and having an inclined surface formed to broaden toward the downstream side of the combustion chamber; and a plurality of air jet ports formed in the inclined surface of the annular bulkhead and adapted to jet air into the combustion chamber.

Gas turbine combustor and fuel supply method used for the same

A combustor includes a chamber mixing and burning fuel and air and an air hole plate disposed on a wall surface of the chamber. The air hole plate includes a plurality of rows disposed concentrically of a plurality of air holes jetting coaxial jets of fuel and air into the chamber. A first fuel nozzle and a second fuel nozzle are disposed near a fuel hole for jetting fuel into an air hole row on an inner peripheral side. The first fuel nozzle is structured to suppress turbulence of surrounding air flow and the second fuel nozzle is structured to promote turbulence of a surrounding air flow. In accordance with the aspect of the present invention, good flame stability can be maintained while further reducing NOx in a combustor using coaxial jets.

Combustor having a first plurality of fuel nozzles having a first cross-sectional shape and a second plurality of fuel nozzles having a second cross-sectional shape different than the first cross-sectional shape

A combustor and a combustion method for the combustor, which can suppress backfire and ensure stable combustion. The combustor comprises a mixing-chamber forming member for forming therein a mixing chamber in which air for combustion and fuel are mixed with each other, and a combustion chamber for burning a gas mixture mixed in the mixing chamber and producing combustion gases. A channel for supplying the air for combustion to the mixing chamber from the outer peripheral side of the mixing-chamber forming member is provided inside the mixing-chamber forming member. The fuel and the air are premixed in the channel, and a resulting premixed gas mixture is supplied to the mixing chamber.

Combustor comprising a member including a plurality of air channels and fuel nozzles for supplying fuel into said channels

A gas turbine combustor for mixing fuel into combustion air introduced from a compressor, burning an air-fuel mixture, and supplying produced combustion gas to a gas turbine. The combustor has a liquid fuel nozzle for jetting out liquid fuel and a pre-mixture chamber wall having a hollow conical shape gradually spreading in the direction in which the fuel is jetted out from the liquid fuel nozzle, and defining a pre-mixture chamber therein. A plurality of gaseous fuel nozzles are disposed around the pre-mixture chamber wall in an opposing relation respectively to a plurality of air inlet holes bored through the pre-mixture chamber wall and jet out gaseous fuel substantially coaxially with the axes of the air inlet holes.

Gas turbine combustor and fuel supply method for same

A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet.

Burner and gas turbine combustor

A combustor includes two upstream parts of fuel supply system supplying gaseous fuels of two types having different heating values from each other, a three-way fuel transfer valve merging the two upstream parts of fuel supply system with each other, a plurality of gaseous fuel supply subsystems supplying a combustion chamber with the gaseous fuels supplied through the three-way fuel transfer valve and branched, and a plurality of burners injecting, corresponding to each of the gaseous fuel supply subsystems, the gaseous fuel supplied from the gaseous fuel supply subsystem into the combustion chamber.

Gas turbine combustor and gaseous fuel supply method for gas turbine combustor

A combustor includes a chamber mixing and burning fuel and air and an air hole plate disposed on a wall surface of the chamber. The, air hole plate includes a plurality of rows disposed concentrically of a plurality of air holes jetting coaxial jets of fuel and air into the chamber. A first fuel nozzle and a second fuel nozzle are disposed near a fuel hole for jetting fuel into an air hole row on an inner peripheral side. The first fuel nozzle is structured to suppress turbulence of a surrounding air flow and the second fuel nozzle is structured to promote turbulence of a surrounding air flow. In accordance with the aspect of the present invention, good flame stability can be maintained while further reducing NOx in a combustor using coaxial jets.

Combustor and a fuel supply method for the combustor

The present invention improves the reliability of a combusting system including multiple combustors and improves an environmental performance thereof. The invention includes a device that delays the start time of fuel injection from a fuel nozzle of a combustor including a ignitor from the start time of fuel injection from a fuel nozzle of the combustor not including the ignitor.

Combusting system, remodeling method for combusting system, and fuel injection method for combusting system

A combustor comprises a liquid fuel nozzle for injecting liquid fuel to a combustion chamber, and an air supply nozzle disposed around the liquid fuel nozzle and injecting air. The air supply nozzle is disposed such that air is injected from the air supply nozzle in a direction toward an axis of the liquid fuel nozzle. A space is formed around an outlet of the liquid fuel nozzle, through which the liquid fuel is injected from the liquid fuel nozzle to the combustion chamber, upstream of a distal end of the outlet in a direction in which the liquid fuel is injected. Carbonaceous deposits on surrounding surfaces of the outlet of the liquid fuel nozzle can be suppressed regardless of the operating conditions of a combustor.

Combustor, gas turbine combustor, and air supply method for same

A gas turbine combustor includes a liquid fuel nozzle for jetting out liquid fuel; a pre-mixture chamber wall provided with the liquid fuel nozzle at a center thereof, having a hollow conical shape gradually spreading in the direction in which the fuel is jetted out, and defining a pre-mixture chamber therein; a plurality of air inlet holes bored through the pre-mixture chamber wall and introducing the combustion air to the pre-mixture chamber such that angles at which the combustion air is introduced to the pre-mixture chamber through the air inlet holes are deflected at least toward the circumferential direction of the pre-mixture chamber wall; and a plurality of gaseous fuel nozzles disposed around the pre-mixture chamber wall in an opposing relation respectively to the plurality of air inlet holes and jetting out gaseous fuel substantially coaxially with axes of the air inlet holes.

Combustor and combustion method for combustor

The plant includes a gaseous fuel processing apparatus for pre-processing natural gas (gaseous fuel) produced in the gas field, a liquid fuel processing apparatus for pre-processing liquid fuel obtained during the extraction and refining process of the natural gas, and a gas turbine. The gas turbine includes a compressor for generating compressed air, a combustor for mixing the compressed air from the compressor with one or both of the gaseous fuel pre-processed by the gaseous fuel processing apparatus and the liquid fuel pre-processed by the liquid fuel processing apparatus, and for burning a gas mixture, and a turbine for driving a generator by combustion gases supplied from the combustor.

Gas turbine power generating machine

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Mito, Japan

Hiroshi Inoue